阅读说明：本技术 涡轮风扇发动机及包括其的飞行器 (Turbofan engine and aircraft comprising same ) 是由 帕斯卡尔·加尔代斯 弗雷德里克·里德赖 利昂内尔·恰普拉 于 2019-06-24 设计创作，主要内容包括：本发明提出了一种涡轮风扇发动机及包括其的飞行器,所述涡轮风扇发动机包括马达和围绕所述马达的短舱,其中,所述短舱与所述马达之间限定用于旁通流的管道,并且空气流在所述管道中流动,所述短舱包括反向器翻转板(104),其中,每个反向器翻转板在收起位置与展开位置之间铰接运动,在所述收起位置,所述反向器翻转板不处于所述旁通管道中,在所述展开位置,所述反向器翻转板横过所述旁通管道,所述涡轮风扇发动机的特征在于,至少一个反向器翻转板(104)具有旨在在所述展开位置允许空气流动的至少一个泄露窗口(400,410),并且其特征在于,所述至少一个反向器翻转板(104)具有横过所述泄露窗口(400,410)延伸的至少一个翅片(402,412)。(The invention proposes a turbofan engine and an aircraft comprising it, the turbofan engine comprising a motor and a nacelle surrounding the motor, wherein the nacelle and the motor define between them a duct for bypass flow and in which an air flow flows, the nacelle comprising reverser flaps (104), wherein each reverser flap is hingedly movable between a stowed position, in which it is not in the bypass duct, and a deployed position, in which it crosses the bypass duct, the turbofan engine being characterized in that at least one reverser flap (104) has at least one leakage window (400, 410) intended to allow air flow in the deployed position, and in that the at least one reverser flap (104) has a flow cross-over window (400, 410) at least one fin (402, 412) extending.)

1. A turbofan engine (100) comprising a motor (20) and a nacelle (102) surrounding the motor (20), wherein the nacelle (102) and the motor (20) define therebetween a duct (202) for a bypass flow (208) and in which air flows, the nacelle (102) comprising reverser flaps (104), wherein each reverser flap is hingedly movable between a stowed position, in which the reverser flap is not in the bypass duct (202), and a deployed position, in which the reverser flaps traverse the bypass duct (202), at least one reverser flap (104) having at least one leakage window (400, 410, 810, 910) intended to allow air flow in the deployed position, and characterized in that, the at least one reverser flap plate (104) having at least one fin (402, 412, 612, 712, 812, 912) extending across the leakage window (400, 410, 810, 910), wherein the leakage window (410, 910) is constituted by a hole through the reverser flap (104), and wherein each fin (712) is in the form of a first plane (712a) and a second plane (712b) continuing from the first plane (712a), characterized in that the first plane (712a) is perpendicular to the plane of the reverser flap panel (104) and is delimited by a perforated face of the reverser flap panel (104), and in that the second plane (712b) is inclined relative to the plane of the reverser flap panel (104) and extends from and beyond the rearwardly facing perforated face of the reverser flap panel (104).

2. The turbofan engine (100) of claim 1 wherein the leakage window (810) is in the form of a notch through the reverser flap plate (104) at a downstream edge of the reverser flap plate (104).

3. The turbofan engine (100) of claim 1, wherein the leakage window (410,490) is formed by a hole through the reverser flap plate (104) at a mid-position of the reverser flap plate (104).

4. An aircraft (10) comprising at least one turbofan engine (100) according to one of the preceding claims.

Technical Field

The present invention relates to a turbofan engine comprising a nacelle equipped with a plurality of reverser flaps provided with vortex generating means, and to an aircraft comprising at least one such turbofan engine.

Background

The aircraft includes a fuselage with wings fixed to each side of the fuselage. At least one turbofan engine is suspended beneath each airfoil. Each turbofan is fixed under the wing by means of a suspension pylon fixed between the structure of the wing and the structure of the turbofan.

The turbofan engine includes a motor, and a nacelle secured around the motor and a fan located forward of the motor. The nacelle and the motor define a bypass duct through which air flows from front to back, passing through the fan to generate thrust.

The nacelle includes a plurality of reverser flipping panels. The reverser flaps are arranged around the bypass duct and each is movable in a rotational sense on the structure of the nacelle between a stowed position, in which it is not in the bypass duct, and a deployed position, in which it is positioned across the bypass duct so as to redirect the air flow from the bypass duct to the outside through a window provided for this purpose. Typically, the window houses a cascade for redirecting the bypass air flow forward for generating reverse thrust.

Due to the power of the fan, the air in the bypass duct flows at high speed.

The operating gap around each reverser flap creates a passage through which air can escape, resulting in a rearward flow when the reverser flaps are in the deployed position.

These leakages and high speeds of air generate a residual thrust towards the rear of the jet engine which acts in opposition to the braking effect sought by deploying the reverser flaps, and it is therefore desirable to find a solution by which the effect of these leakages can be limited.

Disclosure of Invention

The object of the present invention is to propose a turbofan engine comprising a nacelle equipped with a plurality of reverser flaps provided with vortex generating means.

To this end, the invention proposes a turbofan engine comprising a motor and a nacelle surrounding the motor, wherein the nacelle and the motor define between them a duct for a bypass flow and in which an air flow flows, the nacelle comprising reverser flaps, wherein each reverser flap is hingedly movable between a stowed position, in which it is not in the bypass duct, and a deployed position, in which it crosses the bypass duct, characterized in that at least one reverser flap has at least one leakage window intended to allow the flow of air in the deployed position, and in that it has at least one fin extending across the leakage window, wherein the leakage window is constituted by a hole through the reverser flap plate and wherein each fin is in the form of a first plane and a second plane continuing from the first plane, characterized in that the first plane is perpendicular to and bounded by the perforated face of the reverser flap plate, and in that the second plane is inclined relative to and extends from and beyond the rearwardly facing perforated face of the reverser flap plate.

Jet engines of this type can reduce the effect of leakage around the reverser turning plates by the presence of fins that convert the air flow from leakage to low energy vortices.

Advantageously, the leakage window is constituted by a space extending around the reverser flap.

Advantageously, the leakage window is constituted by a hole passing through the reverser flap at a middle position of the reverser flap.

Advantageously, the leakage window is in the form of a notch through the reverser flap at a downstream edge of the reverser flap.

The invention also proposes an aircraft comprising at least one turbofan according to one of the above variants.

Drawings

The above-mentioned and other features of the present invention will become more apparent upon reading the following description of an exemplary embodiment, which is given with reference to the accompanying drawings, in which:

figure 1 is a side view of an aircraft comprising a jet engine according to the invention,

figure 2 is a perspective view of a jet engine according to the invention,

figure 3 is a cross-sectional side view through a jet engine in a deployed position,

figure 4 is a front view of a reverser roll-over panel according to a particular embodiment of the invention in a deployed position,

figure 5 is a cross-sectional view of the reverser flipping panel according to a particular embodiment of the invention along the line V-V of figure 4,

figure 6 is a view similar to figure 5 of another embodiment of the invention,

figure 7 is a view similar to figure 5 of another embodiment of the invention,

FIG. 8 is a view similar to FIG. 4 of another embodiment of the invention, and

fig. 9 is a view similar to fig. 4 of another embodiment of the present invention.

Detailed Description

Fig. 1 shows an aircraft 10 comprising a fuselage 12 to each side of which is fixed a wing 14 carrying at least one turbofan 100 according to the invention. The turbofan engine 100 is secured beneath the wing 14 by a hanger bracket 16.

FIG. 2 illustrates a turbofan engine 100 having a nacelle 102 and a motor 20 housed within nacelle 102, and including a fan casing 206. In this case, the motor 20 is represented by its nose cone and its fan 22 within the air inlet of the nacelle 102.

In the following description, and by convention, X denotes a longitudinal axis of the turbofan engine 100, which is parallel to a longitudinal or roll axis of the aircraft 10 and is oriented forward towards the front of the turbofan engine 100, a lateral axis parallel to a pitch axis of the aircraft, which is horizontal when the aircraft is on the ground, and Z denotes a vertical axis parallel to a yaw axis when the aircraft is on the ground, the three directions X, Y and Z being mutually orthogonal and forming an orthogonal frame of reference whose origin is the centre of gravity of the turbofan engine 100. In the following description, the position-related terms refer to the front and rear of the jet engine 100, which also correspond to the front and rear of the aircraft 10.

Fig. 3 shows the nacelle 102 in a cross-sectional view in the deployed position of the reverser roll-over panel.

Turbofan engine 100 has a duct 202 between nacelle 102 and motor 20 in which a bypass flow 208 from the air intake and through fan 22 flows, and which therefore flows in a forward to aft flow direction.

Nacelle 102 has a stationary structure that includes, among other things, a fan housing 206.

Nacelle 102 has an aft fairing 207 that forms the nozzle wall. The nacelle 102 supports the reverser flap 104 and has an openwork structure that forms a window 210 (fig. 3) around the reverser flap 104.

The nacelle 102 thus comprises a plurality of reverser flaps 104 distributed over the periphery of the nacelle 102 and inside it according to the angular opening of the window 210 about the longitudinal axis X.

Each reverser roll-over panel 104 is mounted on the structure of the nacelle 102 in an articulated motion between a stowed position and a deployed position, and vice versa. The transition from the stowed position to the deployed position is caused by rotation of the reverser roll-over panel 104 towards the interior of the jet engine 100.

In the stowed position, each reverser roll-over panel 104 is not in the bypass duct 202 and closes the area of the window 210. In the deployed position, the reverser roll over panel 104 is positioned across the bypass duct 202 and out of the way of the window 210, allowing the bypass flow 208 to pass through, and the reverser roll over panel 104 then extends toward the motor 20.

A cascade 225 may be provided across the window 210 to direct the forwardly redirected air flow.

Each reverser flap 104 is hinged to the structure of the nacelle 102 on the hinge 212 by an edge downstream with respect to the flow direction, while the opposite free edge is positioned in the upstream direction in the stowed position and is positioned towards the motor 20 in the deployed position.

The transition from the stowed position to the deployed position (and vice versa) is achieved by any suitable means known to those skilled in the art. In the embodiment of the invention presented herein, for each reverser roll-over panel 104, the nacelle 102 comprises: a carriage 214 mounted for translational movement parallel to the longitudinal axis X with respect to the structure of the nacelle 102; a lever 216 mounted in an articulated manner between the carrier 214 and the reverser roll-over plate 104; and an activation system (e.g., a jack) provided for moving the carrier 214 forward and rearward to transition the reverser roll-over panels 104 from the stowed position to the deployed position, and vice versa.

Fig. 4 shows the reverser roll-over panels 104 in the deployed position. When two reverser roll-over panels 104 are side-by-side, they are spaced apart from each other so as to maintain a space 400 that allows the roll-over panels to operate without interacting with each other.

This space 400 thus opens a path for a portion of the bypass airflow 208 that may pass through this space 400 and towards the exhaust nozzle of the jet engine 100. The space 400 thus forms a leakage window 400 through which a portion of the bypass airflow 208 flows in the deployed position.

As shown in fig. 4, at least one of the reverser flaps 104 comprises a leakage window 400, 410 provided to allow air to flow in the deployed position, and the leakage window 400, 410 may be a leakage window 400 constituted by a space extending around the reverser flap 104 or a leakage window 410 constituted by a hole through the reverser flap 104. Of course there may be one or the other or both of these leakage windows 400, 410.

In order to define the portion of the bypass flow 208 force that passes through the leakage windows 400, 410, means for generating a vortex behind the reverser flap 104 are arranged across said leakage windows 400.

Fig. 5 shows a cross-sectional view of the reverser flipping panel 104.

The vortex generating means is in the form of fins 402, 412 extending across the leakage windows 400, 410. The vortices generated by the fins 402, 412 disrupt the flow of air and thereby lose force.

Fig. 8 shows a variation in the location of the leakage window. In this embodiment of the invention, the leakage window 810 is in the form of a notch through the reverser flap plate 104 at the downstream edge of the reverser flap plate 104. Fins 812 are also positioned across the leakage window 810.

Fig. 9 shows a variant in which the number of leakage windows and the positions of the leakage windows are different. In this embodiment of the invention there are two leakage windows 910 and each leakage window 910 is in the form of a hole through the reverser flap 104. Fins 912 are also positioned across the leakage window 910.

Fig. 5 to 7 show different types of fins which may be used across the leakage window in the form of holes through the reverser flaps 104. These different types of fins may also be used in the context of the leakage windows of fig. 8 and 9.

In the embodiment of fig. 5, each fin 412 is in the form of a plane inclined with respect to the plane of the reverser flap plate 104, wherein the fins 412 are delimited by the perforated face of the reverser flap plate 104. The plane of the reverser flap plate 104 is the mid-plane between the planes of the perforated faces of the reverser flap plate 104.

In the embodiment of fig. 6, each fin 612 is in the form of a plane inclined with respect to the plane of the reverser flap plate 104, which fin is delimited on the one hand by the forwardly facing perforated face of the reverser flap plate 104 and on the other hand extends beyond the rearwardly facing perforated face of the reverser flap plate 104.

In the embodiment of fig. 7, each fin 712 is in the form of a first plane 712a and a second plane 712b that continues from the first plane 712 a. The first plane 712a is perpendicular to the plane of the reverser flap panel 104 and is bounded by the perforated face of the reverser flap panel 104, and the second plane 712b is inclined relative to the plane of the reverser flap panel 104 and extends from and beyond the rearwardly facing perforated face of the reverser flap panel 104.

Of course, the various embodiments described above can be combined as desired, for example by combining different types of leakage windows, arranging multiple leakage windows in each reverser flap 104, using different types of fins.

Although the invention has been described in more detail in the context of a nacelle beneath a wing, the invention can be applied to a nacelle located at the rear of a fuselage.

In the embodiment of the invention presented here, the reverser flaps 104 are mounted so as to be able to move only in the sense of rotation, but it may be provided that the reverser flaps are mounted on slides which are able to move in translation and are fixed to the rear fairing 207. The mobile slider and the aft fairing 207 are then retracted before transitioning to the deployed position.

The surface area of the leakage windows 400, 410, 810, 910 preferably constitutes 5% to 30% of the surface area of the reverser flap 104.

In the embodiment of fig. 7, the angle α between the first plane 712a and the second plane 712b is preferably between 5 ° and 45 °.

In the embodiment of fig. 6 and the embodiment of fig. 7, the length of the planes 612, 712b located beyond the rearward facing perforated face of the reverser flipping panel 104 is preferably between 5mm and 30 mm.