阅读说明：本技术 用于包括反推力装置的双涵道涡轮机的机舱，包括这种机舱的双涵道涡轮机，以及包括至少一个这种涡轮机的飞行器 (Nacelle for a dual-ducted turbine comprising a thrust reverser, dual-ducted turbine comprising such a nacelle, and aircraft comprising at least one such turbine ) 是由 纪尧姆·格莱玛瑞克 昆汀·马蒂亚斯·伊曼纽尔·加诺德 于 2020-03-13 设计创作，主要内容包括：本发明涉及一种用于飞行器双涵道涡轮机(100)的机舱(10A),该机舱包括：·环形外壳(11),该环形外壳围绕纵向轴线(104)延伸,·反推力装置(13),该反推力装置包括：·环形的可移动整流罩(14),该环形的可移动整流罩位于环形外壳的下游并能够在关闭位置和打开位置之间沿着纵向轴线相对于环形外壳滑动,在该打开位置,整流罩和机舱壳体在彼此之间限定出开口,·至少一个第一反推力叶栅(15),·致动机构,该致动机构被设计成使得能够用于反推力装置的部分或全部推力消除构型,在部分或全部推力消除构型中,可移动整流罩(14)移动到其打开位置,同时将该第一叶栅或每个第一叶栅(15)保持在其缩回位置,开口(17)被反推力装置的至少一个第二推力减小叶栅(23)占据,以使得穿过开口的次级流以使穿过开口的次级流沿着纵向轴线产生大致为零的推力或正推力而定向的速度出现在机舱的外部。(The invention relates to a nacelle (10A) for an aircraft dual-ducted turbine (100), comprising: -an annular casing (11) extending around a longitudinal axis (104), -a thrust reverser (13) comprising: -an annular movable cowl (14) located downstream of the annular casing and able to slide along the longitudinal axis with respect to the annular casing between a closed position and an open position in which the cowl and the nacelle casing define an opening between each other, -at least one first thrust reverser cascade (15), -an actuating mechanism designed so as to be able to be used in a partial or total thrust canceling configuration of the thrust reverser, in which the movable cowl (14) is moved to its open position while keeping the or each first cascade (15) in its retracted position, the opening (17) being occupied by at least one second thrust reducing cascade (23) of the thrust reverser so that the secondary flow passing through the opening emerges outside the nacelle at a speed such that the secondary flow passing through the opening generates substantially zero thrust or positive thrust along the longitudinal axis.)

1. A nacelle (10A) for an aircraft dual-ducted turbine (100) in which an intake air flow (101) flows in an upstream to downstream direction, the nacelle being divided into a primary flow channel and a secondary flow channel (105), the nacelle (10A, 10B, 10C) comprising:

-a stationary annular housing (11) extending around a longitudinal axis (104) of the nacelle,

-a counterthrust device (13) comprising:

an annular movable cowl (14) extending around the longitudinal axis (104) and located downstream of the annular casing (11), the movable cowl (14) being slidable along the longitudinal axis (104) with respect to the annular casing (11) between a closed position, in which the movable cowl (14) and the annular casing (11) jointly define an annular and continuous outer surface (16) of the nacelle (10A, 10B, 10C), and an open position, in which the movable cowl (14) and the annular casing (11) define between them an opening (17) oriented radially with respect to the longitudinal axis (104), the opening (17) extending circumferentially around the longitudinal axis (104),

at least one first movable thrust reverser cascade (15) able to occupy a retracted position, in which the movable cowl (14) is in the closed position, and an extended position, in which the movable cowl (14) is in the open position, the first cascade being housed inside the annular casing (11), the first cascade extending across the opening (17) so that at least part of the secondary flow is able to pass through the first cascade in the extended position so as to emerge outside the nacelle (10A) at a speed oriented so that at least part of the secondary flow generates a negative thrust along the longitudinal axis (104),

the movable cowl (14) and the or each first cascade (15) being connected to an actuating mechanism capable of moving the movable cowl and the or each first cascade together,

the nacelle (10A) being characterized in that the actuating mechanism is designed so as to be able to be used in a partial or complete thrust-canceling configuration of the thrust reverser (13), in the partial or full thrust canceling configuration, the movable cowl (14) is moved to an open position of the movable cowl, while maintaining the or each first cascade (15) in a retracted position of the or each first cascade, and in which said opening (17) is occupied by at least one second thrust reducing cascade (23) of said thrust reverser (13), such that the secondary flow through the opening (17) occurs outside the nacelle at a velocity directed such that the secondary flow through the opening generates substantially zero thrust or positive thrust along the longitudinal axis (104).

2. The nacelle (10A) of claim 1, wherein said actuation mechanism is designed to:

-selectively moving the movable cowl (14) and the one or more first cascades (15) by sliding them along the longitudinal axis (104) respectively from the closed position to the open position and from the retracted position to the extended position;

-selectively retaining said one or more first cascades (15) in said retracted position and selectively moving said movable cowl by sliding said movable cowl (14) along said longitudinal axis (104) between said closed position and said open position.

3. The nacelle (10A) as set forth in claim 2, wherein said actuating mechanism includes at least one first actuator (22) designed to slide said movable cowl (14) along said longitudinal axis (104) between said closed position and said open position.

4. The nacelle (10A) as claimed in claim 3, wherein said actuating mechanism comprises at least one first blocking member (24) designed to block, in a first blocking position, the sliding of said one or more first cascades (15) with respect to said movable cowl (14) along said longitudinal axis (104), and to unblock, in a second blocking position, said one or more first cascades (15) so that they can slide with respect to said movable cowl (14) along said longitudinal axis (104).

5. The nacelle (10A) as claimed in claim 3 or claim 4, wherein said actuating mechanism comprises at least one second blocking member (25) designed to unblock said one or more first cascades (15) in a third blocking position, so that they can slide along said longitudinal axis (104) with respect to said annular casing (11), and to block said one or more first cascades (15) from sliding along said longitudinal axis (104) with respect to said annular casing (11) in a fourth blocking position, said one or more first cascades (15) being in said retracted position.

6. The nacelle (10A) as claimed in any of claims 1 to 5, wherein the or each second thrust reducing cascade (23) is designed to:

-selectively occupying a retracted position in which the or each second thrust reducing cascade is housed inside the annular casing (11) of the nacelle, the second cascade (23) in the retracted position being radially superposed with the first cascade (15) with respect to the longitudinal axis (104) when the movable cowl (14) is in the closed position;

-selectively remain in the retracted position when the movable cowl (14) and the first cascade (15) slide respectively from the closed position to the open position and from the retracted position to the extended position;

-selectively sliding along the longitudinal axis (104) from the retracted position to an extended position, with respect to the annular casing (11) of the nacelle, when the first cascade (15) is in the retracted position and when the movable cowl (14) slides from the closed position to the open position, in which the second cascade (23) occupies the opening (17) defined between the movable cowl (14) and the annular casing (11).

7. The nacelle (10A) as claimed in claim 6, wherein one or more second cascades (23) are arranged radially outside said one or more first cascades (15) with respect to said longitudinal axis (104).

8. The nacelle (10A) as claimed in claim 6 or claim 7, wherein said actuation mechanism is designed to:

-selectively keeping said one or more second cascades (23) in said retracted position and selectively moving said movable cowl (14) and said one or more first cascades (15) by sliding them along said longitudinal axis (104) from said closed position to said open position and from said retracted position to said extended position, respectively;

-selectively keeping said one or more first cascades (15) in said retracted position and selectively moving said movable cowl (14) and said one or more second cascades (23) by sliding them along said longitudinal axis (104) from said closed position to said open position and from said retracted position to said extended position, respectively.

9. The nacelle (10A) of any of claims 6 to 8, wherein said actuation mechanism comprises at least one first blocking member (24) designed to:

-on the one hand, in a first blocking position to block the sliding of the one or more first cascades (15) with respect to the movable cowl (14) along the longitudinal axis (104), and in a second blocking position to unblock the one or more first cascades (15) so that the one or more first cascades can slide with respect to the movable cowl (14) along the longitudinal axis (104); and

-on the other hand, unblocking the one or more second cascades (23) in the first blocking position such that the one or more second cascades are slidable along the longitudinal axis (104) with respect to the movable cowl (14), and blocking the one or more second cascades (23) from sliding along the longitudinal axis (104) with respect to the movable cowl (14) in the second blocking position.

10. The nacelle (10A) of any of claims 6 to 9, wherein said actuating mechanism comprises at least one second blocking member (25) designed to:

-on the one hand, unblocking the one or more first cascades (15) in a third blocking position such that the one or more first cascades are slidable along the longitudinal axis (104) with respect to the annular casing (11), and blocking the one or more first cascades (15) from sliding along the longitudinal axis (104) with respect to the annular casing (11) in a fourth blocking position, the one or more first cascades (15) being in the retracted position;

-on the other hand, in the third blocking position, to block the one or more second cascades (23) from sliding along the longitudinal axis (104) with respect to the annular casing (11), the one or more second cascades (23) being in the retracted position, and in the fourth blocking position, to unblock the one or more second cascades (23), so that the one or more second cascades can slide along the longitudinal axis (104) with respect to the annular casing (11).

11. An aircraft dual-ducted turbine (100) comprising, from upstream to downstream along the axial direction of the gas flow, a fan (102) and a separation nozzle from which emerge an annular main flow channel, called main flow path, and an annular secondary flow channel (105), called secondary flow path, surrounding said main flow path, furthermore the turbine (100) is streamlined by a nacelle (10A, 10B, 10C) according to any of claims 1 to 10.

12. An aircraft comprising at least one dual-ducted turbine according to claim 11.

Technical Field

The present invention relates to a nacelle for a dual-ducted turbine comprising a thrust reverser, to a dual-ducted turbine comprising such a nacelle, and to an aircraft comprising at least one such turbine.

Background

In general, an aircraft dual-ducted turbine comprises a fan for taking in an air flow which, downstream of the fan, is divided into a primary air flow which flows in a primary flow channel, called primary flow path, within a core of the turbine and a secondary air flow which bypasses the core in a secondary flow channel, called secondary flow path.

In the main flow path, the main gas flow flows in an upstream to downstream direction through a low pressure compressor, a high pressure compressor, a combustor, a high pressure turbine, a low pressure turbine, and an exhaust nozzle. In the secondary flow path, the secondary airflow may flow through the guide vane assembly.

Both the primary and secondary flows contribute to the overall thrust of the turbine, which is therefore particularly high.

The turbine is also streamlined through a nacelle (carnene) which surrounds the secondary flow path and defines upstream an air intake through which the air flow enters the turbine.

While it is advantageous to generate such high total thrust during certain phases of flight of the aircraft and at certain turbine speeds, this is often problematic during other phases of flight and at other speeds (e.g., at idle speed).

This is the case, for example, in the following cases: this is the landing phase when the aircraft is near the ground and is idling, making it difficult for the aircraft to quickly descend to the ground.

This is also the case during the landing phase when the aircraft has landed on the runway. More specifically, in order to reduce the braking distance of the aircraft on the runway, the braking of the aircraft must be supplemented with a thrust reverser mounted on the nacelle of the turbine. To this end, the thrust reverser is designed to discharge the airflow flowing along the secondary flow path to the outside by directing it upstream of the nacelle and thus generate a thrust reversal or negative thrust.

However, the use of thrust reversers only allows the speed of the aircraft to exceed a predetermined speed limit, for example 60 knots (111.12 km/h). Below this speed limit, the risk of the turbine again sucking in the air flow discharged by the thrust reverser upstream of the nacelle is too great, and moreover, the risk of sucking in debris from the runway thrown by the air flow discharged by the thrust reverser is too great, both of which can cause damage to the turbine.

Braking of the aircraft is required to keep the aircraft stationary when it is stationary on the ground, or even when the aircraft is taxiing on a runway, on the ground, braking of the aircraft alone enables the speed of the aircraft to be adjusted, as is the case when the use of thrust reversers is limited to aircraft speeds that exceed a speed limit.

Disclosure of Invention

The present invention aims to overcome the above-mentioned drawbacks by proposing a nacelle for an aircraft dual-ducted turbine comprising a thrust reverser capable of operating in a thrust reversal mode on the one hand and in a partial or total thrust cancellation mode on the other hand.

More specifically, the invention relates to a nacelle for an aircraft dual-ducted turbine in which an intake air flow flows in an upstream to downstream direction, the nacelle being divided into a primary flow channel and a secondary flow channel, the nacelle comprising:

a stationary annular housing extending around a longitudinal axis of the nacelle,

-a thrust reverser device comprising:

an annular movable cowl extending about a longitudinal axis and downstream of the annular housing, the movable cowl being slidable along the longitudinal axis relative to the annular housing between a closed position, in which the movable cowl and the annular housing together define an annular and continuous outer surface of the nacelle, and an open position, in which the movable cowl and the annular housing define an opening between the movable cowl and the annular housing that is oriented radially with respect to the longitudinal axis, the opening extending circumferentially about the longitudinal axis,

-at least one first movable thrust reverser cascade able to occupy a retracted position, in which the movable cowl is in the closed position, the first cascade being housed inside the annular casing, and an extended position, in which the movable cowl is in the open position, the first cascade extending across the opening so that at least a portion of the secondary flow can pass through the first cascade in the extended position so as to emerge outside the nacelle at a velocity such as to direct at least a portion of the secondary flow along the longitudinal axis with a negative thrust,

the movable cowl and the or each first cascade are connected to an actuating mechanism capable of moving the movable cowl and the or each first cascade together, said actuating mechanism being further designed so as to be able to be used in a partial or complete thrust cancellation configuration of the thrust reverser, in which the movable cowl is moved to an open position of the movable cowl while maintaining the or each first cascade in a retracted position of the or each first cascade, in which the opening is occupied by at least one second thrust-reducing cascade of the thrust reverser, so that the secondary flow passing through the opening emerges outside the nacelle at a speed oriented so that the secondary flow passing through the opening generates substantially zero thrust or positive thrust along the longitudinal axis.

According to alternative embodiments, these embodiments may be employed together or separately:

one or more first cascades are designed to send the airflow flowing in a direction from upstream to downstream along the secondary flow path to the outside of the nacelle and upstream;

-the one or more first cascades of blades forming a first angle of between 110 ° and 150 °, in particular equal to 120 °, with the longitudinal axis, the radially inner ends of the blades being located downstream with respect to the longitudinal axis and the radially outer ends of the blades being located upstream with respect to the longitudinal axis;

one or more second cascades are designed to send the airflow flowing in the direction from upstream to downstream along the secondary flow path to the outside and downstream of the nacelle;

-the one or more second cascades of blades forming a second angle of between 30 ° and 60 °, in particular equal to 45 °, with the longitudinal axis, the radially inner ends of the blades being located upstream with respect to the longitudinal axis and the radially outer ends of the blades being located downstream with respect to the longitudinal axis;

the thrust reverser further comprises at least one reverser door designed to move from a retracted position, in which the reverser door or doors are used to unblock the secondary flow path, to an extended position, in which the reverser door or doors are used to axially block the secondary flow path, when the fairing slides from the closed position to the open position;

the actuating mechanism is designed to:

selectively moving the movable fairing and the one or more first cascades along the longitudinal axis from a closed position to an open position and from a retracted position to an extended position, respectively;

selectively retaining the one or more first cascades in a retracted position and selectively moving the movable cowling by sliding it along the longitudinal axis between a closed position and an open position;

the actuating mechanism comprises at least one first actuator designed to slide the movable cowl along the longitudinal axis between a closed position and an open position;

the actuating mechanism comprises at least one first blocking member designed to block, in a first blocking position, the sliding of the one or more first cascades with respect to the movable cowl along the longitudinal axis and to unblock, in a second blocking position, the sliding of the one or more first cascades with respect to the movable cowl along the longitudinal axis, so that the sliding of the one or more first cascades with respect to the movable cowl along the longitudinal axis is possible;

the actuating mechanism comprises at least one second blocking member designed to unblock the one or more first cascades in a third blocking position so that the one or more first cascades can slide along the longitudinal axis with respect to the annular casing, and to block the one or more first cascades from sliding along the longitudinal axis with respect to the annular casing in a fourth blocking position, the one or more first cascades being in a retracted position;

the or each second thrust reducing cascade is designed to:

selectively occupying a retracted position in which the or each second thrust reducing cascade is housed inside an annular casing of the nacelle, said second cascade in the retracted position radially overlapping the first cascade with respect to the longitudinal axis when the movable cowl is in the closed position;

selectively remaining in the retracted position when the movable cowl and the first cascade slide respectively from the closed position to the open position and from the retracted position to the extended position;

omicron, selectively slides along the longitudinal axis with respect to the annular shell of the nacelle from a retracted position to an extended position, when the first cascade is in the retracted position and when the movable cowl slides from the closed position to the open position, in the extended position the second cascade occupying the opening defined between the movable cowl and the annular shell.

-the one or more second cascades are arranged radially outside the one or more first cascades with respect to the longitudinal axis;

the actuating mechanism is designed to:

selectively maintaining the one or more second cascades in a retracted position and selectively moving the movable fairing and the one or more first cascades by sliding them along the longitudinal axis from a closed position to an open position and from a retracted position to an extended position, respectively;

selectively maintaining the one or more first cascades in a retracted position and selectively moving the movable fairing and the one or more second cascades along the longitudinal axis from a closed position to an open position and from the retracted position to an extended position, respectively;

the actuating mechanism comprises at least one first blocking member designed to:

in one aspect, in the first blocking position, the one or more first cascades are blocked from sliding relative to the movable cowl along the longitudinal axis, and in the second blocking position, the one or more first cascades are unblocked so that the one or more first cascades can slide relative to the movable cowl along the longitudinal axis; and

in another aspect, unblocking the one or more second cascades in the first blocking position such that the one or more second cascades are slidable along the longitudinal axis relative to the movable cowl, and blocking the one or more second cascades from sliding along the longitudinal axis relative to the movable cowl in the second blocking position;

the actuating mechanism comprises at least one second blocking member designed to:

in one aspect, unblocking the one or more first cascades in the third blocking position such that the one or more first cascades are slidable along the longitudinal axis relative to the annular housing, and blocking the one or more first cascades from sliding along the longitudinal axis relative to the annular housing in the fourth blocking position, the one or more first cascades being in the retracted position;

in another aspect, in a third blocking position, the one or more second cascades are blocked from sliding relative to the annular housing along the longitudinal axis, the one or more second cascades are in a retracted position, and in a fourth blocking position, the one or more second cascades are unblocked such that the one or more second cascades can slide relative to the annular housing along the longitudinal axis.

The invention also relates to an aircraft double-ducted turbine comprising, from upstream to downstream along the axial direction of the gas flow, a fan and a separation nozzle from which emerge an annular main flow channel, called main flow path, and an annular secondary flow channel, called secondary flow path, surrounding the main flow path, the turbine furthermore being streamlined by the nacelle as described above.

The invention also relates to an aircraft comprising at least one dual-ducted turbine as described above.

Drawings

Other aspects, objects, advantages and features of the invention will be better understood by reading the following detailed description of a non-limiting preferred embodiment of the invention, which is provided for purposes of illustration, with reference to the accompanying drawings, in which:

FIG. 1 is a longitudinal section view of an aircraft dual-ducted turbine comprising a thrust reverser operating in direct injection mode, according to an embodiment of the invention;

FIG. 2 is a longitudinal section view of the dual-ducted turbine shown in FIG. 1, wherein the thrust reverser is operating in thrust reversal mode;

FIG. 3 is a longitudinal section view of the dual-ducted turbine shown in FIGS. 1 and 2, wherein the counterthrust device operates in a partial thrust cancellation mode;

FIG. 4 is a longitudinal section view of the dual-ducted turbine shown in FIGS. 1 to 3, wherein the counterthrust device operates in a full thrust cancellation mode;

FIG. 5 is a view of the dual-ducted turbine shown in FIG. 1 along a cross-sectional plane A-A;

figure 6 is a detailed longitudinal section view of the thrust reverser shown in figures 1 to 4, with the second blocking member in the third blocking position;

figure 7 is a detailed longitudinal section view of the thrust reverser shown in figures 1 to 4, with the second blocking member in a fourth blocking position;

FIG. 8 is a longitudinal section view of an aircraft dual-ducted turbine comprising a thrust reverser operating in direct injection mode, according to another embodiment of the invention;

FIG. 9 is a perspective view of the aircraft dual-ducted turbine shown in FIG. 8, wherein the thrust reverser is operating in a direct injection mode;

figure 10 is a longitudinal section view of the double-ducted turbine shown in figures 8 and 9, wherein the thrust reverser operates in thrust reversal mode;

FIG. 11 is a perspective view of the dual ducted turbine shown in FIGS. 8 and 9, wherein the thrust reverser is operating in a thrust reversal mode;

FIG. 12 is a longitudinal section view of the dual-ducted turbine shown in FIGS. 8 to 11, wherein the counterthrust device operates in a partial thrust cancellation mode;

figure 13 is a longitudinal section view of the dual-ducted turbine shown in figures 8 to 12, with the thrust reverser operating in full thrust cancellation mode;

FIG. 14 is a perspective view of the dual ducted turbine shown in FIGS. 8 to 13, wherein the thrust reverser is operating in a full thrust canceling mode;

figure 15 is a perspective view of an aircraft dual-ducted turbine comprising a thrust reverser operating in direct injection mode, according to another embodiment of the invention.

Detailed Description

Fig. 1 to 7 show an aircraft dual-ducted turbine 100 comprising a nacelle 10A according to an embodiment of the invention. Fig. 8 to 14 show a turbine 100 comprising a nacelle 10B according to another embodiment of the invention. FIG. 15 shows a turbine 100 including a nacelle 10C according to another embodiment of the invention. Components common to the three embodiments of the invention have the same reference numerals.

First, an axial direction, a radial direction orthogonal to the axial direction, and a circumferential direction orthogonal to the axial direction and the radial direction are defined.

The turbine 100 comprises, from upstream to downstream along the direction of the air flow in the axial direction, a fan 102 and a separation nozzle (not shown) from which emerge an annular main flow channel (not shown), called main flow path, formed in a core 103 of the turbine 100 extending along an axially oriented longitudinal axis 104, and an annular secondary flow channel 105, called secondary flow path, surrounding the main flow path (fig. 1 and 8). Primary and secondary flow paths 105 are centered on longitudinal axis 104. The nacelle 10A, 10B, 10C surrounding the turbine 100 comprises an annular intake lip 101, inside which the intake flow 101 flows towards a fan 102.

The primary flow path itself includes, in an upstream to downstream direction, a low pressure compressor, a high pressure compressor, a combustor, a high pressure turbine, a low pressure turbine, and an exhaust nozzle. The secondary flow path 105 includes a guide vane assembly 106 (fig. 1 and 8) that includes vane blades for rectifying flow from the fan 102.

The airflow flowing along each of the primary and secondary flow paths contributes to the overall thrust of the turbomachine 100.

The turbine 100 is also streamlined by a nacelle 10A, 10B, 10C having an annular shape extending around a longitudinal axis 104 and around a secondary flow path 105.

The nacelle 10A, 10B, 10C comprises an outer annular housing 11 extending around a longitudinal axis 104 and forming a continuous outer surface of the nacelle 10A, 10B, 10C. The annular casing 11 of the nacelle 10A, 10B, 10C is formed by a fairing or by a plurality of assembled fairings and constitutes a stationary casing extending in the upstream to downstream direction from the annular air intake lip 101 to a portion of the annular casing 11 housing the sliding cascades 15, 23 of the thrust reverser 13.

The inner surface 12 of the nacelle 10A, 10B, 10C is formed, for example, by an outer shell surrounding a fan casing 11a of the fan 102 and an intermediate casing 11B located downstream of the fan 102. Thus, the annular casing 11 surrounds the fan housing 11a and the intermediate housing 11 b. The intermediate housing 11b also supports, for example, a guide vane assembly 106.

The turbine 100 has, for example, a high bypass ratio, in particular a bypass ratio of more than 10. This bypass ratio, also referred to as "BPR", corresponds to the conventional meaning of the term, in particular as defined by the European Aviation Safety Agency (EASA), namely: "ratio of air mass flow through the ducted duct of the gas turbine engine to air mass flow through the engine core calculated at maximum thrust when the engine is stationary in the international standard atmosphere at sea level".

The nacelle 10A, 10B, 10C further comprises a thrust reverser 13, in turn comprising at least one first thrust cascades 15 and an annular movable cowl 14 extending around the longitudinal axis 104 and downstream of the annular casing 11 of the nacelle 10A, 10B, 10C. The movable cowling 14 is also located downstream of the outer shell of the intermediate shell 11b, where appropriate.

The movable cowl 14 is movable by sliding with respect to the annular casing 11, which is fixed along the longitudinal axis 104 between a closed position and an open position.

In the closed position (fig. 1, 8 and 15), the movable cowl 14 and the annular housing 11 together define a continuous annular outer surface 16. The term "continuous surface" is understood to mean that, in the closed position, the upstream outer edge of the movable cowl 14 and the downstream outer edge of the annular casing 11 are in contact with each other along their entire circumference around the longitudinal axis 104.

In the open position (fig. 2-4 and 10-14), the movable cowl 14 and the annular casing 11 define a radial opening 17 therebetween relative to the longitudinal axis 104, the radial opening extending circumferentially about the longitudinal axis 104. Thus, the outer surface 16 defined by the movable cowl 14 and the annular casing 11 is no longer continuous, and the upstream outer edge of the movable cowl 14 and the downstream outer edge of the annular casing 11 are longitudinally spaced apart from each other such that the upstream outer edge of the movable cowl and the downstream outer edge of the annular casing define the opening 17. In the open position, the airflow from the secondary flow path 105 is discharged to the outside through the opening 17 formed between the movable cowling 14 of the thrust reverser 13 and the annular casing 11.

For example, the first cascades 15 of thrust reversers 13 are evenly distributed around the longitudinal axis 104. Each of the first blade rows 15 occupies an angular sector about the longitudinal axis 104.

The first cascade 15 is movable. The first cascade is also designed such that:

selectively occupy the retracted position when the movable cowl 14 is in the closed position;

selectively sliding along the longitudinal axis 104 with respect to the annular casing 11 from the retracted position to the extended position when the movable cowl 14 itself slides from the closed position to the open position, and from the extended position to the retracted position when the movable cowl 14 in turn slides from the open position to the closed position;

selectively occupy the retracted position when the movable cowl 14 slides between the closed position and the open position.

In the retracted position (fig. 1, 4, 5, 8, 9 and 12 to 14), the first cascade 15 is housed inside the annular casing 11. Thus, the annular housing 11 surrounds the first cascade 15. In this manner, no airflow from secondary flow path 105 passes through first cascade 15.

When the movable cowl 14 is in the closed position and the first cascade 15 is in the retracted position, the thrust reverser 13 is in the first condition and operates in the direct injection mode (fig. 1, 8, 9 and 15).

In the extended position (fig. 2, 10 and 11), the first cascade 15 is located outside the annular casing 11 and, in the open position, it closes the opening 17 defined between the annular casing 11 and the movable cowl 14. The first cascade 15 extends across said opening 17.

When the movable cowl 14 is in the open position and the first cascade 15 is in the extended position, the thrust reverser 13 is in the second condition and operates in thrust reversal mode (fig. 2, 10 and 11). The airflow from the secondary flow path 105 is discharged to the outside through the first cascade 15, which directs the airflow upstream of the nacelle 10A, 10B, 10C. Thus, a portion of the airflow from secondary flow path 105 passes through first cascade 15 to emerge outside of nacelle 10A, 10B, 10C at a velocity directed such that the portion of the airflow generates a negative thrust along longitudinal axis 104. Thus, in the second state, the thrust reverser 13 receives the airflow flowing along the secondary flow path 105 to generate thrust directed upstream of the nacelle 10A, 10B, 10C. The term "negative thrust" is understood to mean a thrust force directed opposite to the direction of forward movement of the aircraft.

Thus, when the thrust reverser 13 is in the second condition, the first cascade 15 is designed to receive the airflow from the secondary flow path 105 and to send it outside and upstream of the nacelle 10A, 10B, 10C.

To this end, the first cascade has blades which form, for example, a first angle of between 110 ° and 150 °, in particular equal to 120 °, with the longitudinal axis 104, the radially inner ends of the blades being located downstream with respect to the longitudinal axis 104 and the radially outer ends of the blades being located upstream with respect to the longitudinal axis 104. Therefore, the blades are inclined from upstream to downstream in the axial direction, and from the outside to the inside in the radial direction.

When the movable cowl 14 is in the open position and the first cascade 15 is in the retracted position, the thrust reverser 13 is in the third condition and operates in thrust canceling mode (fig. 4, 13 and 14). The third state corresponds to a thrust canceling configuration, which may be a full or partial thrust canceling configuration, as described below.

When the thrust reverser 13 is in the third state, the airflow from the secondary flow path 105 is discharged to the outside via the opening 17 defined between the annular casing 11 and the movable cowl 14, without being redirected upstream of the nacelle 10A, 10B, 10C via the first cascade 15. Thus, in the third condition, the thrust reverser 13 receives the airflow flowing in the secondary flow path 105, so as to dissipate and therefore eliminate the thrust generated by said airflow, without generating thrust reversals or negative thrust.

In the third condition, for example, the opening 17 defined between the annular casing 11 and the movable cowling 14 is left clear, so that the airflow from the secondary flow path 105 passes through the opening 17 so as to appear outside the nacelle 10A, 10B, 10C at a speed oriented so that it generates substantially zero thrust along the longitudinal axis 104 (fig. 12, 13 and 14). The airflow from the secondary flow path 105 is discharged substantially radially to the outside through the opening 17 defined between the annular casing 11 and the movable cowl 14.

Alternatively, the opening 17 may be occupied by at least one second movable thrust reducing cascade 23, as explained in more detail in the following description, so that the airflow from the secondary flow path 105 passes through the opening 17 so as to emerge outside the nacelle 10A, 10B, 10C (fig. 3 and 4) at a velocity oriented so that it generates a positive thrust along the longitudinal axis 104.

Thus, thrust reverser 13 acts only on the airflow flowing along secondary flow path 105.

In addition to the first, second and third conditions, the thrust reverser 13 may of course be in any intermediate condition between the first and second conditions and between the first and third conditions, so that a smaller portion of the airflow from the secondary flow path 105 is discharged to the outside through the opening 17, another portion of the airflow escaping axially from the secondary flow path 105 to generate thrust, whether or not this opening is closed by the first cascade 15.

This allows, for example, the thrust reverser 13 to operate in a partial thrust canceling mode (fig. 3 and 12), instead of in a full thrust canceling mode (fig. 4, 13 and 14) corresponding to the third condition of the thrust reverser 13. In both cases, the counterthrust device 13 is in a partial or total thrust cancellation configuration. In this manner, the thrust generated by the airflow axially escaping from secondary flow path 105 may be modulated. Partial thrust cancellation is of concern, for example, to dissipate an unnecessary portion of the thrust generated by airflow escaping axially from secondary flow path 105 during aircraft maneuvering.

In this way, the thrust reverser 13 can be operated in a partial or full thrust canceling mode without allowing thrust reversal operation, in order to overcome the difficulties associated with the high thrust generated by the turbomachine 100 acting as a dual-ducted turbine.

This is the case, for example, in the following cases: this is the case when, during the landing phase when the aircraft is close to the ground and is idling, the anti-thrust device 13 of the turbomachine 100 fitted to the aircraft can be operated in a partial thrust cancellation mode to accelerate the descent of the aircraft. The same applies to the flight phase, in an emergency situation where a rapid descent is required.

The same is true during the landing phase when the aircraft has landed on the runway. If the speed of the aircraft is below a predetermined speed limit, for example 60 knots (111.12km/h), the aircraft-mounted thrust reverser 13 of the turbomachine 100 may operate in a partial or full thrust canceling mode without the risk of re-breathing in the exhaust air flow or of breathing in debris from the runway.

This is still to ensure that the aircraft remains stationary on the ground, or even in the case of taxiing phases on a runway, the aircraft-equipped thrust reverser 13 of the turbomachine 100 can operate in a partial or total thrust-canceling mode without the risk of re-breathing in exhaust air flow or debris from the runway.

The operation of the anti-thrust device 13 of the turbomachine 100 fitted to the aircraft in the partial thrust cancellation mode during the descent or landing phase also makes it possible to prevent the turbomachine 100 from supplying the aircraft with power not required by the aircraft and which must be dissipated in any case when the aircraft is braking on the ground.

Furthermore, since the thrust reverser 13 can operate in partial or full thrust canceling mode, it is possible to increase the idle speed of the turbomachine 100, which on the one hand increases the reliability of the turbomachine 100 and on the other hand makes it easier for the aircraft to obtain the necessary power requirements.

The partial or total thrust cancellation operation of the anti-thrust device 13 fitted to the aircraft of one of the turbines 100 may also enable the aircraft to manoeuvre in flight or on the ground, since the total thrust generated by each of the turbines 100 is no longer equal. This will also reduce the size of the vertical stabilizer of the aircraft.

Conversely, in flight, when the total thrust produced by each of the turbines is not equal, some or all of the thrust cancellation operations of the thrust reverser 13 fitted to the aircraft of one of the turbines 100 may enable the total thrust produced by each of the turbines 100 to be rebalanced.

Operation of the thrust reverser 13 in partial or full thrust cancellation mode is also less restrictive in terms of authentication than operation in thrust reversal mode.

The thrust reverser 13 also comprises at least one reverser door 18.

The reversing door 18 is designed to move from a retracted position to a deployed position when the movable cowl 14 slides from a closed position to an open position.

In the first condition of the thrust reverser 13, the tailgate 18 is in the retracted position (fig. 1, 8, 9 and 15) when the thrust reverser 13 operates in the direct injection mode. In the second and third conditions of the thrust reverser 13, the tailgate 18 is in the deployed position when the thrust reverser 13 operates in thrust reversal or thrust cancellation mode (fig. 2, 4, 10, 11, 13 and 14).

In the retracted position, reversing gate 18 axially unblocks secondary flow path 105. The reversing door 18 is accommodated in the movable cowl 14, for example. Thus, the airflow flows from upstream to downstream along secondary flow path 105 and escapes axially from the secondary flow path.

In the deployed position, the reversing gate 18 is disposed in the secondary flow path 105 and, in particular, axially blocks the secondary flow path 108 downstream of the guide vane assembly 106. Accordingly, reversing gate 18 closes secondary flow path 105 and prevents airflow flowing along secondary flow path 105 from escaping axially from the secondary flow path. Accordingly, the reversing gate 18 enhances the discharge of airflow from the secondary flow path 105 through the opening 17 defined between the annular housing 11 and the movable cowling 14 in the open position.

For example, the tailgate 18 is moved between a retracted position and a deployed position by the movable cowl 14 as the movable cowl slides between the closed position and the open position.

To this end, the reversing doors 18 may each be mounted on the movable cowl 14 such that the reversing doors pivot about a circumferentially oriented pivot axis (not shown) between the retracted and deployed positions. The reversing gate 18 may also be guided by a pivotally mounted link 19 such that the reversing gate pivots about a circumferentially oriented pivot axis (not shown) on the reversing gate 18 on the one hand and on the annular inner shell 107 of the turbine 100, which extends about the longitudinal axis 104 and is surrounded by the secondary flow path 105 and the nacelles 10A, 10B, 10C on the other hand.

The thrust reverser 13 can also comprise at least one guide member 20 supported by the annular casing 11 and designed to guide the first cascade 15 so that it slides along the longitudinal axis 104 between a retracted position and an extended position (fig. 5, 6, 7, 10, 12 and 13).

To this end, the guide members 20 are each formed by an axial guide rail oriented parallel to the longitudinal axis 104. Furthermore, the rails 20 are evenly distributed about the longitudinal axis 104.

Each first cascade 15 is guided by a guide rail 20, for example, at each of its circumferential ends.

Furthermore, each guide rail 20 serves, for example, to guide the adjacent circumferential ends of two first blade rows 15, so that the guide rail 20 is thus sandwiched between two circumferentially adjacent first blade rows 15.

The thrust reverser 13 also comprises an actuating mechanism designed to:

selectively moving the movable cowl 14 and the first cascade 15 by sliding them along the longitudinal axis 104 from the closed position to the open position and from the retracted position to the extended position, respectively, on the one hand, and from the open position to the closed position and from the extended position to the retracted position, respectively, on the other hand;

selectively maintaining the first cascade 15 in the retracted position and selectively moving the movable cowl by sliding the movable cowl 14 along the longitudinal axis 104 between the closed position and the open position.

Thus, the actuation mechanism causes the thrust reverser 13 to operate selectively in a thrust reversal mode (fig. 2, 10 and 11) or in a full thrust or partial thrust cancellation mode (fig. 3, 4, 12, 13 and 14).

The actuating mechanism of the thrust reverser 13 comprises, for example, at least one first actuator 22 designed to slide the movable cowl 14 along the longitudinal axis 104 between a closed position and an open position (fig. 8 to 14 and 15).

The first actuator 22 is supported by the annular housing 11, for example.

The first actuator 22 comprises, for example, cylinders extending axially and evenly distributed about the longitudinal axis 104.

The cylinders of the first actuator 22 may be hydraulic, pneumatic or electric.

According to a first embodiment of the invention (not shown), in the third condition of the thrust reverser 13, the opening 17 defined between the annular casing 11 and the movable cowl 14 remains clear, and the actuating mechanism also comprises at least one first blocking member designed to block, in a first blocking position, the sliding of the first cascade 15 with respect to the movable cowl 14 along the longitudinal axis 104, and to unblock, in a second blocking position, the first cascade 15 so that it can slide with respect to the movable cowl 14 along the longitudinal axis 104.

In this way, when the first blocking member is in the first blocking position, the first cascade 15 and the movable cowl 14 slide together as a single piece along the longitudinal axis 104. Thus, when the first actuator 22 slides the movable cowl 14 from the closed position to the open position, the movable cowl 14 in turn slides the first cascade 15 from the retracted position to the extended position. This enables the thrust reverser 13 to switch from the first state to the second state and thus operate in thrust reversal mode.

Conversely, when the first blocking member is in the second blocking position, the movable cowl 14 and the first cascade 15 are free to slide relative to each other along the longitudinal axis 104. Thus, the first cascade 15 can be maintained in the retracted position when the first actuator 22 slides the movable cowl 14 from the closed position to the open position. This enables the counterthrust device 13 to switch from the first state to the third state and thus to operate in the thrust cancellation mode.

For example, a pair of first blocking members is provided for each first cascade 15 so as to block said first cascade 15 with respect to the movable cowl 14 at each of the two circumferential ends of the first cascade in the first blocking position.

For example, each of the first blocking members comprises a main body supported by the movable cowl 14 and a finger mounted such that it slides with respect to the main body along a sliding axis oriented radially with respect to the longitudinal axis 104 between a first blocking position and a second blocking position.

In the first blocking position, the fingers engage in openings coaxial to the sliding axis and formed in the first cascade 15.

In the second blocking position, the fingers unblock the opening of the first cascade 15.

The first blocking member is actuated, for example, hydraulically, pneumatically, electrically or magnetically. The first blocking members may also be mechanically actuated by means of a cable or loop connected to each of the first blocking members.

The actuating mechanism further comprises, for example, at least one second blocking member designed to unblock the first cascade 15 in a third blocking position so that the first cascade can slide along the longitudinal axis 104 with respect to the annular casing 11, and to block the first cascade 15 from sliding along the longitudinal axis 104 with respect to the annular casing 11 in a fourth blocking position, the first cascade 15 being in the retracted position.

In this way, when the second blocking member is in the third blocking position, the first cascade 15 is free to slide along the longitudinal axis 104 with respect to the annular housing 11. Thus, when the first blocking member is in the first blocking position and when the first actuator 22 slides the movable cowl 14 from the closed position to the open position, the movable cowl 14 in turn slides the first cascade 15 from the retracted position to the extended position. This enables the thrust reverser 13 to switch from the first state to the second state and thus operate in thrust reversal mode.

Conversely, when the second blocking member is in the fourth blocking position, the first cascade 15 is fixed with respect to the annular casing 11 and is in the retracted position. Thus, when the first blocking member is in the second blocking position and when the first actuator 22 slides the movable cowl 14 between the closed position and the open position, the first cascade 15 remains in the retracted position. This enables the counterthrust device 13 to switch from the first state to the third state and thus to operate in the thrust cancellation mode.

For example, a pair of second blocking members is provided for each first cascade 15 so that, in the fourth blocking position, the first cascade 15 is blocked with respect to the annular casing 11 at each of both circumferential ends of the first cascade.

For example, each of the second blocking members comprises a main body supported by the annular housing 11, in particular by one of the rails 20, and a finger mounted so that it slides with respect to the main body along a sliding axis oriented radially with respect to the longitudinal axis 104 between the third blocking position and the fourth blocking position.

In the third blocking position, the fingers unblock the following openings: the opening is coaxial with the sliding axis and is formed in the first cascade 15 guided by the guide rail 20, in particular in the circumferential end of the first cascade guided by the guide rail 20.

In the fourth blocking position, the finger engages in an opening of the first cascade 15 guided by the guide rail 20, in particular in a circumferential end of the first cascade guided by the guide rail 20.

The second blocking member is actuated, for example, hydraulically, pneumatically, electrically or magnetically. The second blocking members may also be mechanically actuated by means of a cable or loop connected to each of the second blocking members.

Thus, according to the first embodiment, when the thrust reverser 13 operates in the thrust reversal mode, the first actuator 22 slides the movable cowl 14 from the closed position to the open position, the movable cowl 14 in turn sliding, on the one hand, the first cascade 15 from the retracted position to the extended position (with the first blocking member in the first blocking position), and, on the other hand, pivoting the tailgate 18 from the retracted position to the extended position. When the movable cowling 14 reaches the open position, when the first cascade 15 reaches the extended position and when the reversing door 18 reaches the deployed position, the thrust reverser 13 is in the second condition and the airflow flowing along the secondary flow path 105 blocked by the reversing door 18 is discharged to the outside through the first cascade 15 in the extended position, which directs said airflow upstream of the nacelle, generating a thrust directed upstream of the nacelle.

When the thrust reverser 13 operates in the full-thrust or partial-thrust cancellation mode, the first actuator 22 slides the movable cowl 14 from the closed position to the open position, the movable cowl 14 in turn pivots the tailgate 18 from the retracted position to the deployed position, while the first cascade 15 is held in the retracted position by the second blocking member in the fourth blocking position. When the movable cowl 14 reaches the open position and when the reversing gate 18 reaches the deployed position (in which the first cascade 15 is kept in the retracted position), the thrust reverser 13 is in the third condition and the airflow flowing along the secondary flow path 105 blocked by the reversing gate 18 is discharged substantially radially to the outside, practically without thrust or thrust, through the opening 17 defined between the annular casing 11 and the movable cowl 14 in the open position. In other words, the thrust generated is substantially zero.

According to a second embodiment of the invention, illustrated in fig. 1 to 7, the thrust reverser 13 also comprises at least one second thrust reducing cascade 23, which, in a third condition of the thrust reverser 13, occupies the opening 17 defined between the annular casing 11 and the movable cowl 14.

For example, the second cascades 23 are evenly distributed around the longitudinal axis 104. Each of the second cascades 23 occupies an angular sector around the longitudinal axis 104.

The thrust reverser 13 comprises, for example, the same number of first cascades 15 and second cascades 23.

The second vane cascade 23 is movable. The second cascade is also designed such that:

selectively occupy the retracted position when the movable cowl 14 is in the closed position;

selectively occupy the retracted position when the movable cowl 14 and the first cascade 15 slide between the closed position and the open position and between the retracted position and the extended position, respectively; and

selectively sliding along the longitudinal axis 104 from a retracted position to an extended position with respect to the annular casing 11 when the first cascade 15 is in the retracted position and when the movable cowl 14 slides from the closed position to the open position, and selectively sliding along the longitudinal axis from an extended position to a retracted position with respect to the annular casing when the first cascade 15 is in the retracted position and when the movable cowl 14 slides from the open position to the closed position.

In the retracted position (fig. 1 and 2), the second cascade 23 is housed in the annular casing 11 around the second cascade and radially superposed with the first cascade 15 with respect to the longitudinal axis 104. Thus, no airflow from secondary flow path 105 passes through second cascade 23.

When the movable cowl 14 is in the closed position, when the first cascade 15 is in the retracted position, and when the second cascade 23 is in the retracted position, the thrust reverser 13 is in the first state and operates in the direct injection mode (fig. 1).

When the movable cowl 14 is in the open position, when the first cascade 15 is in the extended position, and when the second cascade 23 is in the retracted position, the thrust reverser 13 is in the second condition and operates in thrust reversal mode (fig. 2).

In the extended position (fig. 4), the second shutter 23 is located outside the annular casing 11 and closes the opening 17 defined between the annular casing 11 and the movable cowl 14 in the open position. Thus, the second cascade 23 extends across said opening 17.

When the movable cowling 14 is in the open position, when the first cascade 15 is in the retracted position, and when the second cascade 23 is in the extended position, the counterthrust device 13 is in the third condition and operates in thrust canceling mode (fig. 4). The airflow from the secondary flow path 105 is discharged to the outside through the second cascade 23, which guides the airflow downstream of the nacelle 10A. Thus, airflow from secondary flow path 105 passes through opening 17 and emerges outside nacelle 10B at a velocity oriented such that the airflow generates a positive thrust along longitudinal axis 104. Therefore, in the third state, the thrust reverser 13 receives the airflow flowing in the secondary flow path 105 so as to cancel the thrust generated by the airflow without generating thrust. The term "positive thrust" is understood to mean a thrust force directed in the same direction as the forward movement of the aircraft.

When the thrust reverser 13 is in the third condition, the second cascade 23 is therefore designed to receive the airflow coming from the secondary flow path 105 and to send it outside and downstream of the nacelle 10A.

To this end, the second cascade 23 has blades forming a second angle of between 30 ° and 60 °, in particular equal to 45 °, with the longitudinal axis 104, the radially inner ends of the blades being located upstream with respect to the longitudinal axis 104 and the radially outer ends of the blades being located downstream with respect to the longitudinal axis 104. Therefore, the blades are inclined from upstream to downstream in the axial direction and from the inside to the outside in the radial direction.

The second cascade 23 is arranged radially outside the first cascade 15, for example with respect to the longitudinal axis 104. When the thrust reverser is in the first state (fig. 1), the second cascade 23 is clamped between the annular casing 11 and the first cascade 15, for example radially with respect to the longitudinal axis 104. This helps to separate the flow exiting through the second cascade 23 and thus create disturbances in the flow which help to eliminate the thrust of the turbine 100.

The guide member 20 is designed, for example, to guide the first cascade 15 and the second cascade 23, on the one hand such that the first cascade slides along the longitudinal axis 104 between a retracted position and an extended position, and on the other hand such that the second cascade slides along the longitudinal axis 104 between a retracted position and an extended position (fig. 5, 6 and 7).

To this end, the guide members 20 are each formed by an axial guide rail oriented parallel to the longitudinal axis 104. Furthermore, the rails 20 are evenly distributed about the longitudinal axis 104.

Each pair of superimposed first 15 and second 23 cascades is guided, for example, by the same guide rail 20.

Further, each guide rail 20 is used, for example, to guide adjacent circumferential ends of two first blade rows 15 on the one hand and adjacent circumferential ends of two second blade rows 23 that are stacked with the first blade rows 15 on the other hand, and therefore, the guide rail 20 is sandwiched between each pair of circumferentially adjacent and stacked first and second blade rows 15 and 23.

According to a second embodiment, the actuation mechanism is designed to:

selectively keeping the second cascade 23 in the retracted position and selectively moving the movable cowl 14 and the first cascade 15 by sliding them along the longitudinal axis 104 from the closed position to the open position and from the retracted position to the extended position, respectively, on the one hand, and from the open position to the closed position and from the extended position to the retracted position, respectively, on the other hand;

selectively keeping the first cascade 15 in the retracted position and selectively moving the movable cowling and the second cascade by sliding the movable cowling 14 and the second cascade 23 along the longitudinal axis 104 from the closed position to the open position and from the retracted position to the extended position, respectively, on the one hand, and from the open position to the closed position and from the extended position to the retracted position, respectively, on the other hand.

The actuating mechanism thus enables the thrust reverser 13 to be selectively operated in the thrust reverser mode (fig. 2) or in the thrust canceling mode (fig. 4).

The actuating mechanism further comprises at least one first blocking member 24, designed to:

on the one hand, in the first blocking position (fig. 2) to block the first cascade 15 from sliding relative to the movable cowl 14 along the longitudinal axis 104, and in the second blocking position (fig. 3 and 4) to unblock the first cascade 15 so that it can slide relative to the movable cowl 14 along the longitudinal axis 104; and

on the other hand, in the first blocking position (fig. 2) the second cascade 23 is unblocked so that it can slide along the longitudinal axis 104 with respect to the movable cowl 14, and in the second blocking position (fig. 3 and 4) the second cascade 23 is blocked from sliding along the longitudinal axis 104 with respect to the movable cowl 14.

In this way, when the first blocking member 24 is in the first blocking position (fig. 2), the first cascade 15 and the movable cowl 14 slide together as a single piece along the longitudinal axis 104, while the movable cowl 14 and the second cascade 23 slide freely with respect to each other along the longitudinal axis 104. Thus, when the first actuator 22 slides the movable cowl 14 from the closed position to the open position, the movable cowl 14 in turn slides the first cascade 15 from the retracted position to the extended position, the second cascade 23 being able to remain in the retracted position. This enables the thrust reverser 13 to switch from the first state to the second state and thus operate in thrust reversal mode.

Conversely, when the first blocking member 24 is in the second blocking position (fig. 3 and 4), the movable cowl 14 and the first cascade 15 slide freely relative to each other along the longitudinal axis 104, while the second cascade 23 and the movable cowl 14 slide together as a single piece along the longitudinal axis 104. Thus, when the first actuator 22 slides the movable cowl 14 from the closed position to the open position, the movable cowl 14 in turn slides the second cascade 23 from the retracted position to the extended position, the first cascade 15 being able to remain in the retracted position. This enables the counterthrust device 13 to switch from the first state to the third state and thus to operate in the thrust cancellation mode.

For example, a pair of first blocking members 24 is provided for each pair of superimposed first and second cascades 15, 23, in order to block said first cascades 15 with respect to the movable cowl 14 in a first blocking position on the one hand and to block said second cascades 23 with respect to the movable cowl 14 in a second blocking position on the other hand.

For example, each of the first blocking members 24 includes a main body supported by the movable cowl 14 and a finger mounted such that it slides relative to the main body along a sliding axis oriented radially relative to the longitudinal axis 104 between a first blocking position and a second blocking position.

In the first blocking position, the fingers engage in the openings coaxial to the sliding axis and formed in the first cascade 15 and unblock the openings coaxial to the sliding axis and formed in the second cascade 23.

In the second blocking position, the fingers engage in the openings of the second cascade 23 and unblock the openings of the first cascade 15.

The first blocking member 24 is actuated, for example, hydraulically, pneumatically, electrically or magnetically. The first blocking members 24 may also be mechanically actuated by means of a cable or loop connected to each of the first blocking members 24.

The actuating mechanism further comprises, for example, at least one second blocking member 25 designed to:

on the one hand, unblocking the first cascade 15 in the third blocking position (fig. 2 and 6) so that it can slide along the longitudinal axis 104 with respect to the annular casing 11, and blocking the sliding of the first cascade 15 along the longitudinal axis 104 with respect to the annular casing 11 in the fourth blocking position (fig. 3, 4 and 7);

on the other hand, in a third blocking position (fig. 2 and 6) to block the sliding of the second cascade 23 along the longitudinal axis 104 with respect to the annular casing 11, the second cascade 23 is in the retracted position, and in a fourth blocking position (fig. 3, 4 and 7) to unblock the second cascade 23 so that it can slide along the longitudinal axis 104 with respect to the annular casing 11.

In this way, when the second blocking member 25 is in the third blocking position (fig. 2 and 6), the first cascade 15 is free to slide along the longitudinal axis 104 with respect to the annular casing 11, while the second cascade 23 is fixed with respect to the annular casing 11 and is in the retracted position. Thus, when the first blocking member 24 is in the first blocking position and when the first actuator 22 slides the movable cowl 14 from the closed position to the open position, the movable cowl 14 in turn slides the first cascade 15 from the retracted position to the extended position, the second cascade 23 remaining in the retracted position. This enables the thrust reverser 13 to switch from the first state to the second state and thus operate in thrust reversal mode.

Conversely, when the second blocking member 25 is in the fourth blocking position (fig. 3, 4 and 7), the first cascade 15 is fixed and in the retracted position with respect to the annular casing 11, while the second cascade 23 is free to slide along the longitudinal axis 104 with respect to the annular casing 11. Thus, when the first blocking member 24 is in the second blocking position and when the first actuator 22 slides the movable cowl 14 from the closed position to the open position, the movable cowl 14 in turn slides the second cascade 23 from the retracted position to the extended position, the first cascade 15 remaining in the retracted position. This enables the counterthrust device 13 to switch from the first state to the third state and thus to operate in the thrust cancellation mode.

For example, a pair of second blocking members 25 is provided for each pair of superimposed first and second cascades 15, 23, so as to block, on the one hand, said second cascade 23 with respect to the annular casing 11 at each of the two circumferential ends of the second cascade in a third blocking position and, on the other hand, said first cascade 15 with respect to the annular casing 11 at each of the two circumferential ends of the first cascade in a fourth blocking position (fig. 5).

For example, each of the second blocking members 25 comprises a body 251 supported by the annular housing 11, in particular by one of the rails 20, and a finger 252 mounted so that it slides with respect to the body 251 along a sliding axis 253 oriented radially with respect to the longitudinal axis 104, between a third blocking position and a fourth blocking position (fig. 6 and 7).

In the third blocking position (fig. 6), the finger 252 is engaged in an opening 254 coaxial with the sliding axis 253 and formed in the second cascade 23 guided by the guide rail 20, in particular in the circumferential end of the second cascade guided by the guide rail 20. The finger 252 also unblocks an opening 255, which is coaxial with the sliding axis 253 and is formed in the first cascade 15 guided by the guide rail 20, in particular in a circumferential end portion of the first cascade guided by the guide rail 20.

In the fourth blocking position (fig. 7), the finger 252 engages in an opening 255 of the first cascade 15 guided by the guide track 20. The finger 252 also unblocks the opening 254 of the second cascade 23 that is guided by the guide rail 20.

The second blocking member 25 is actuated, for example, hydraulically, pneumatically, electrically or magnetically. The second blocking members 25 may also be mechanically actuated by means of a cable or loop connected to each of the second blocking members 25.

Thus, according to the second embodiment, when the thrust reverser 13 operates in the thrust reversal mode (fig. 2), the first actuator 22 slides the movable cowl 14 from the closed position to the open position, the movable cowl 14 in turn sliding, on the one hand, the first cascade 15 from the retracted position to the extended position (with the first blocking member 24 in the first blocking position), and, on the other hand, the reverser door 18 from the retracted position to the deployed position, while the second cascade 23 is maintained in the retracted position by the second blocking member 25 in the third blocking position. When the movable cowl 14 reaches the open position, when the first cascade 15 reaches the extended position and when the reversing door 18 reaches the deployed position (with the second cascade 23 remaining in the retracted position), the thrust reverser 13 is in the second condition, and the airflow flowing along the secondary flow path 105 blocked by the reversing door 18 is discharged to the outside through the first cascade 15 in the extended position, which directs said airflow upstream of the nacelle 10A, generating a thrust directed upstream of the nacelle 10A.

When the thrust reverser 13 operates in the thrust canceling mode (fig. 4), the first actuator 22 slides the movable cowl 14 from the closed position to the open position, the movable cowl 14 in turn sliding, on the one hand, the second cascade 23 from the retracted position to the extended position (with the first blocking member 24 in the second blocking position), and, on the other hand, pivoting the tailgate 18 from the retracted position to the deployed position, while the first cascade 15 is held in the retracted position by the second blocking member in the fourth blocking position. When the movable cowl 14 reaches the open position, when the second cascade 23 reaches the extended position and when the reversing door 18 reaches the deployed position (in which the first cascade 15 is kept in the retracted position), the thrust reverser 13 is in the third state, and the airflow flowing along the secondary flow path 105 blocked by the reversing door 18 is discharged to the outside through the second cascade 23 in the extended position, which directs the airflow downstream of the nacelle 10A, generating a positive thrust.

According to the third embodiment shown in fig. 8 to 14, in the third condition of the thrust reverser 13, the opening 17 defined between the annular casing 11 and the movable cowl 14 remains open and the first actuator 22 is designed to:

selectively sliding the movable cowl 14 and the first cascade 15 together, on the one hand, along the longitudinal axis 104 from the closed position to the open position and from the retracted position to the extended position, respectively, and, on the other hand, along the longitudinal axis from the open position to the closed position and from the extended position to the retracted position, respectively;

selectively maintaining the first cascade 15 in the retracted position and selectively sliding the movable cowl 14 along the longitudinal axis 104 between the closed position and the open position.

In this way, the first actuator 22 enables the thrust reverser 13 to operate in the thrust reversal mode (fig. 10 and 11) by sliding the movable cowl 14 together with the first cascade 15, and also enables the thrust reverser to operate in the thrust cancellation mode (fig. 13 and 14) by sliding only the movable cowl 14, with the first cascade 15 remaining in the retracted position.

To this end, the first actuator 22 comprises, for example, cylinders extending axially and evenly distributed about the longitudinal axis 104.

Each first cascade 15 is caused to slide by, for example, a single cylinder of the first actuator 22.

The cylinder of the first actuator 22 comprises, for example, two coaxial rods, namely an outer rod 221 and an inner rod 222, which are able to slide with respect to each other. The stroke of the outer rod 221 is also shorter than the stroke of the inner rod 222. The outer bar 221 is mounted so that it can slide axially as a single piece with one of the first cascades 15, while the inner bar 222 is mounted so that it can slide axially as a single piece with the movable cowl 14.

The cylinders of the first actuator 22 may be hydraulic, pneumatic or electric.

Thus, according to the third embodiment, when the thrust reverser 13 operates in the thrust reversal mode (fig. 10 and 11), the first actuator 22 slides the movable cowl 14 from the closed position to the open position, on the one hand, the movable cowl 14 in turn pivoting the reverser doors 18 from the retracted position to the deployed position, and on the other hand, the first cascade 15 from the retracted position to the extended position. When the movable cowl 14 reaches the open position, when the first cascade 15 reaches the extended position and when the counter door 18 reaches the deployed position, the thrust reverser 13 is in the second state, and the airflow flowing along the secondary flow path 105 blocked by the counter door 18 is discharged to the outside through the first cascade 15 in the extended position, which directs said airflow upstream of the nacelle 10B, generating a thrust directed upstream of the nacelle 10B.

When the thrust reverser 13 operates in the thrust canceling mode (fig. 13 and 14), the first actuator 22 slides the movable cowl 14 from the closed position to the open position, the movable cowl 14 in turn pivots the tailgate 18 from the retracted position to the deployed position, while the first actuator maintains the first cascade 15 in the retracted position. When the movable cowl 14 reaches the open position and when the reversing gate 18 reaches the deployed position (in which the first cascade 15 is kept in the retracted position), the thrust reverser 13 is in the third condition and the airflow flowing along the secondary flow path 105 blocked by the reversing gate 18 is discharged to the outside through the opening 17 defined between the annular casing 11 and the movable cowl 14 in the open position, generating practically no thrust or thrust. In other words, the thrust generated is substantially zero.

According to a fourth embodiment, illustrated in fig. 15, in the third condition of the thrust reverser 13, the opening 17 defined between the annular casing 11 and the movable cowl 14 remains clear, and the actuating mechanism comprises at least one second actuator 26 designed to:

selectively sliding the first cascade 15 along the longitudinal axis 104 from the retracted position to the extended position when the first actuator 22 slides the movable cowl 14 along the longitudinal axis 104 from the closed position to the open position, and selectively sliding the first cascade along the longitudinal axis from the extended position to the retracted position when the first actuator 22 slides the movable cowl 14 along the longitudinal axis 104 from the open position to the closed position;

selectively maintaining the first cascade 15 in the retracted position when the first actuator 22 slides the movable cowl 14 along the longitudinal axis 104 between the open position and the closed position.

In this way, the movable cowl 14 and the first cascade 15 are made to slide independently of each other. When the thrust reverser 13 operates in the thrust reversal mode, the first actuator 22 and the second actuator 26 slide the movable cowl 14 and the first cascade 15 simultaneously. In contrast, when the thrust reverser 13 operates in thrust canceling mode, the first cascade 15 remains in the retracted position and only the movable cowl 14 is caused to slide by the first actuator 22.

The second actuator 26 is supported by the annular housing 11, for example.

The second actuator 26 comprises, for example, an axially extending cylinder that is evenly distributed about the longitudinal axis 104.

Each first cascade 15 is caused to slide, for example, by a single cylinder of the second actuator 26.

The cylinder of the second actuator 26 may be hydraulic, pneumatic or electric.

Thus, according to the fourth embodiment, when the thrust reverser 13 operates in the thrust reversal mode, the first actuator 22 slides the movable cowl 14 from the closed position to the open position, the movable cowl 14 in turn pivots the tailgate 18 from the retracted position to the deployed position, and the second actuator 26 slides the first cascade 15 from the retracted position to the extended position. When the movable cowl 14 reaches the open position, when the first cascade 15 reaches the extended position and when the reversing door 18 reaches the deployed position, the thrust reverser 13 is in the second state, and the airflow flowing along the secondary flow path 105 blocked by the reversing door 18 is discharged to the outside through the first cascade 15 in the extended position, which directs said airflow upstream of the nacelle 10C, generating a thrust directed upstream of the nacelle 10C.

When the thrust reverser 13 operates in the thrust canceling mode, the first actuator 22 slides the movable cowl 14 from the closed position to the open position, the movable cowl 14 in turn pivots the tailgate 18 from the retracted position to the deployed position, while the first cascade 15 remains in the retracted position. When the movable cowl 14 reaches the open position and when the reversing gate 18 reaches the deployed position (in which the first cascade 15 is kept in the retracted position), the thrust reverser 13 is in the third condition and the airflow flowing along the secondary flow path 105 blocked by the reversing gate 18 is discharged to the outside through the opening 17 defined between the annular casing 11 and the movable cowl 14 in the open position, generating practically no thrust or thrust. In other words, the thrust generated is substantially zero.