阅读说明：本技术 气体涡轮引擎安装布置结构 (Gas turbine engine mounting arrangement ) 是由 C.H.林 R.G.斯特雷顿 C.T.J.希夫 于 2019-07-18 设计创作，主要内容包括：本公开涉及气体涡轮引擎安装布置结构。提供了一种用于将飞行器气体涡轮引擎安装到飞行器上的安装布置结构。该安装布置结构包括引擎短舱。该引擎短舱包括远侧组件,该远侧组件包括部分环形引擎整流罩、由该引擎整流罩包围的气体涡轮引擎核心外壳、以及在引擎核心外壳和引擎整流罩之间延伸的远侧分叉,该远侧分叉沿第一方向延伸以限定第一轴线。该安装布置结构还包括近侧组件,该近侧组件具有被构造成将该近侧组件安装到引擎核心外壳上的安装架。该近侧组件还包括挂架,该挂架被构造成在引擎安装位置处将该近侧组件安装到安装位置,诸如该飞行器的机翼。(provides a mounting arrangement for mounting an aircraft gas turbine engine to an aircraft, the mounting arrangement including a nacelle including a partial ring shaped engine fairing, a gas turbine engine core casing surrounded by the engine fairing, and a distal prong extending between the engine core casing and the engine fairing, the distal prong extending in a direction to define a axis.)

1, a mounting arrangement for mounting an aircraft gas turbine engine to an aircraft, the mounting arrangement comprising:

a nacelle, the nacelle comprising:

a distal assembly including a partially annular engine cowl, a gas turbine engine core casing surrounded by the engine cowl, and a distal prong extending between the engine core casing and the engine cowl, the distal prong extending in an th direction to define a th axis;

a proximal assembly having a mounting bracket configured to mount the proximal assembly to the engine core casing, the proximal assembly further comprising a pylon configured to mount the proximal assembly to the aircraft at an engine mount location, the pylon extending along a line between the mount location and the engine core casing to define a second axis, wherein the second axis is perpendicular to a surface of the aircraft at the engine mount location and is not parallel to the th axis.

2. The mounting arrangement of claim 1, wherein an angle between the second axis and the th axis is defined between 1 ° and 30 °.

3. The mounting arrangement of claim 1, wherein the proximal assembly comprises a partial annular engine housing configured to abut against a partial annular engine housing of the distal assembly such that the partial annular engine housing of the proximal assembly and the partial annular engine housing of the distal assembly form complete rings when assembled.

4, an aircraft comprising the mounting arrangement of claim 1.

5. The aircraft of claim 4, wherein the aircraft comprises a th engine mounting arrangement mounted to a port side of the aircraft and a second engine mounting arrangement mounted to a starboard side of the aircraft.

6. The aircraft of claim 5, wherein the distal component of each engine mounting arrangement is substantially identical while the proximal components of the -th engine mounting arrangement and the proximal components of the second engine mounting arrangement are mirror images of each other about the axis when assembled.

7. The aircraft of claim 4, wherein the -th axis corresponds to a vertical axis.

8. The aircraft of claim 7, wherein the mounting location comprises a wing of the aircraft.

9. The aircraft of claim 8, wherein the mounting location comprises an upper surface of the wing of the aircraft.

10. The aircraft of claim 8, wherein the mounting location comprises a lower surface of the wing of the aircraft.

11. The aircraft of claim 4, wherein the installation location comprises a fuselage of the aircraft.

12. The aircraft of claim 11, wherein the installation location comprises a tail of the aircraft.

Technical Field

The present disclosure relates to a mounting arrangement for a gas turbine engine.

Background

In many aircraft, the gas turbine engines are mounted in nacelles, known as "nacelles," beneath the wings. A coupling device called a "pylon" mounts each nacelle to the wing.

In many low wing aircraft, the wings are mounted to the fuselage such that the wings are angled relative to the ground with the wing tips being more above the ground than the wing roots. This arrangement is referred to as "dihedral" and is commonly used to provide enhanced aerodynamic stability in roll.

Thus, in these cases, the engine must be mounted to the wing not parallel to the ground. There are two known conventional arrangements for mounting an aircraft engine to a wing having a dihedral.

FIG. 1 shows a left wing 1a of an aircraft having an engine 2a mounted within a nacelle 3 a. A pylon 4a is provided that is mounted to the wing 1a at an angle such that the pylon 4a extends in a vertical direction perpendicular to the ground 5 a. proximal and distal forks 6a and 7a extend from the pylon 4a to couple the engine 2a to the pylon 4a and nacelle 3a, and also extend along a vertical line.

In a second example, the pylon is mounted perpendicular to the distal wing surface such that the Top Dead Center (TDC) of the engine rolls inward toward the fuselage to define an angle α between TDC and the vertical plane V. this arrangement may be referred to as a tilt pylon. such an example is shown in FIG. 2. in FIG. 2, a left wing 1b of the aircraft has an engine 2b mounted within a nacelle 3 b. A pylon 4b is provided that is mounted perpendicular to the distal surface of the wing 1b such that the pylon 4b extends at an angle to the ground 5 b. proximal and distal forks 6b likewise extend from the pylon 4b to couple the engine 2b to the pylon 4b and nacelle 3b and also extend in a line at an angle to the ground 5 b.

Engines mounted over wings are also known (e.g. as Honda)^™HA-420 HondaJet^™As used in (1). Similar problems may arise in the case of wings having dihedral angles.

Disclosure of Invention

According to an th aspect, there is provided a mounting arrangement for mounting an aircraft gas turbine engine to an aircraft, the mounting arrangement comprising:

a nacelle, the nacelle comprising:

a distal assembly including a partially annular engine cowl, a gas turbine engine core casing surrounded by the engine cowl, and a distal prong extending between the engine core casing and the engine cowl, the distal prong extending in an -th direction to define a -th axis;

a proximal assembly having a mounting bracket configured to mount the proximal assembly to the engine core casing, the proximal assembly further comprising a pylon configured to mount the proximal assembly to the aircraft at the engine mount location, the pylon extending along a line between the mount location and the engine core casing to define a second axis, wherein the second axis is perpendicular to a surface of the aircraft at the engine mount location and is non-parallel to the th axis.

Thus, the pylon can be mounted to extend at right angles to the mounting location, while the distal prong of the distal assembly can be mounted to extend at right angles to the ground. Thus, the engine may be mounted within the engine nacelle with the distal bifurcation defining the engine bottom dead center or any other predetermined axis. Thus, the bottom dead center of the engine is coincident for both the port and starboard engines, with a common distal assembly for both engines.

The angle between the second axis and the th axis may be defined to be 1 ° to 30 °.

The proximal assembly may include a partial ring engine casing configured to abut against a partial ring engine casing of the distal assembly such that the partial ring engine casing of the proximal assembly and the partial ring engine casing of the distal assembly form complete rings when assembled.

The engine may be mounted below the wing such that the proximal assembly is mounted above the distal assembly in use.

Alternatively, the engine may be mounted above the wing such that the proximal assembly is mounted below the distal assembly in use.

According to a second aspect of the present invention there is provided an aircraft comprising a mounting arrangement according to aspect .

The aircraft may include an th engine mounting arrangement mounted to a port side of the aircraft and a second engine mounting arrangement mounted to a starboard side of the aircraft.

The distal component of each engine mounting arrangement may be substantially identical, while the proximal component of the th engine mounting arrangement and the proximal component of the second engine mounting arrangement may be mirror images of each other about the th axis when assembled, or may be rotationally derived relative to each other.

The th axis may correspond to a vertical axis.

The mounting location may comprise a wing of the aircraft and may comprise an upper or lower surface of the wing of the aircraft.

Alternatively, the mounting location may comprise a fuselage of the aircraft, and may comprise an aft portion of the aircraft.

In addition, unless mutually exclusive, any feature described herein may be applied to and/or combined with any other feature described herein.

Drawings

Embodiments will now be described, by way of example only, with reference to the accompanying drawings, in which:

FIG. 1 is a schematic front view of an th prior art engine mounting arrangement;

FIG. 2 is a schematic front view of a second prior art engine mounting arrangement;

FIG. 3 is a schematic top view of an aircraft having an engine mounting arrangement;

FIG. 4 is a schematic front view of an th engine mounting arrangement according to the present invention;

FIG. 5 is a schematic front view of a second engine mounting arrangement according to the present disclosure;

FIGS. 6a and 6b are schematic front views of a distal assembly and a proximal assembly, respectively, of the engine mounting arrangement of FIG. 4; and is

FIGS. 7a and 7b are schematic front views of a distal assembly and a proximal assembly, respectively, of the engine mounting arrangement of FIG. 5;

FIG. 8 is a schematic front view of a third engine mounting arrangement according to the present disclosure; and is

Fig. 9 is a schematic front view of a fourth engine mounting arrangement according to the present invention.

Detailed Description

Referring to FIG. 3, an aircraft 10 is shown. The aircraft 10 includes a fuselage 12, a left wing 14a and a right wing 14b, and a tail 70 at the aft end. Mounted to each wing 14a, 14b is a respective engine 16a, 16b, which is mounted by a mounting arrangement shown in more detail in fig. 4 and 5.

Fig. 4 shows a front view of the port engine 16a mounted to the port wing 14a within the nacelle 15 a. As shown, the wing 14a is angled upwardly in a direction extending from the root to the tip along its span. This arrangement is known as dihedral. The amount of dihedral will typically be less than that shown in fig. 4, which is exaggerated to improve clarity.

The airfoil 14a defines an upper surface 18a and a lower surface 20 a. Lower surface 20a defines a spanwise axis 22a that extends parallel to lower surface 20a at an engine mount point 24a of wing 14 a.

A proximal mounting assembly 26a is provided, shown in more detail in FIG. 6b, mounted proximate to the lower surface 20a of the wing 14a and including a pylon 28a, which, when installed, mounts the proximal end of the pylon 28a to the wing 14a at a mounting location 24 a. the distal/radially inner end of the pylon 28a is coupled to a partially annular coupling member 30 a. the coupling member 30a includes -th and second fastener holes 32a, 34a that are circumferentially spaced apart. the coupling member 30a generally includes a spherically connected connecting rod to allow articulation to accommodate manufacturing tolerances, mechanical and thermal displacements.

The proximal mount assembly 26a also includes a partial annular pylon baffle 36 a. the baffle 36a extends from any circumferential surface of the pylon 28a and radially defines gas-washed inner and outer surfaces.

Referring again to fig. 4 and 6b, it can be seen that the pylon 28a extends between the coupling member 30a and the engine mounting point 24a of the wing 14a through the pylon shroud 36a to define a second axis 38a extending between the mounting point 24a and the coupling member 30a the second axis 38a extends perpendicular to the spanwise axis 22a such that the pylon 28a extends perpendicular to the wing distal surface 20a at the mounting point 24a in this embodiment, the vertical axis defines an th axis.

A distal mounting assembly 40a is also provided and is shown in more detail in fig. 6 a. It should be understood that the terms "proximal" and "distal" refer to the relative distance from the surface of the wing on which the engine is mounted, with "proximal" being closer to the wing than "distal". The distal mounting assembly 40a includes an annular engine core housing 42a that surrounds an engine core (not shown). The engine core casing 42a is surrounded by a partial annular cowl 44a configured to house an engine bypass fan (not shown). The engine core casing 42a is mounted to the cowl 44a by a distal bifurcation 46 a. The distal bifurcation 46a extends between the engine core shell 42a and the fairing 44a to define a vertical axis 48a that is perpendicular to the ground 5 when the aircraft 10 is on the ground. Accordingly, the engine equipment disposed within the engine core shell 42a may be located at bottom dead center defined by the distal bifurcation 46a on the port and starboard engines, as will be described in greater detail below.

The distal mounting assembly 40a also includes a coupling member 50a disposed at a top dead center of the engine core housing 42a and having fastener holes 52a, 54 a. A partial annular gap 56a is defined at top dead center of the distal mounting assembly by the space between the ends of the fairing 44 a.

Referring again to FIG. 4, it can be seen how the proximal and distal mounting assemblies 26a, 40a are mounted to , the fastener holes 30a, 32a of the proximal mounting assembly 26a and the fastener holes 52a, 54a of the distal mounting assembly 40a cooperate to allow a fastener, such as a bolt, to pass through to secure the proximal and distal mounting assemblies 26a, 40a at , the pylon 28a is mounted to the wing 14a at a mounting location 24a such that the engine 16a is mounted to the aircraft wing 14 a.

As shown, when the proximal and distal mounting assemblies 26a, 40a are mounted to to form nacelle 15a, the proximal mounting assembly baffle 36a and cowl 44a form a continuous loop to radially define the continuous gas washed inner and outer surfaces of nacelle 15 a.

Referring now to fig. 7a and 7b, a distal mounting assembly 40b and a proximal mounting assembly 26b for a starboard engine 16b are shown, respectively. In fig. 7a and 7b, the same reference numerals are used for the same features, but with "b" attached instead of "a".

As can be seen from a comparison of fig. 6a and 7a, distal mounting assembly 40b is substantially identical to distal mounting assembly 40a, i.e., the location and geometry of each component is substantially identical. Accordingly, a universal distal mount assembly 40a, 40b for both port and starboard engines 16a, 16b may be manufactured.

6a and 6b, once mounted to the wing 14a, the flap 36a will typically be fixed or immovable relative to the wing 14a and the pylon 38a, while the outer tube wall 44a will be hinged to the fixed flap for engine maintenance access, the inner shroud 42a will also be hinged to the proximal structure, either mounted to the pylon (hinged support from structure 30 a) or to the engine (hinged support from 50 a).

Engine servicing located on core casing 42a and cowl 44a latches at the 6 o' clock orientation below top dead center by making the hinges and latch points symmetrical about vertical centerline 48a, cowl will naturally hinge closed, thereby improving the cowl latching process.

However, the proximal mounting assembly 26b for the starboard engine 16b is different than the proximal mounting assembly for the port engine 16a, as shown, the proximal mounting assembly 26b is substantially a mirror image of the proximal mounting assembly 26a about a vertical axis 46b, thus, the generally rotationally symmetric baffle 36b and the coupling member 50b are relatively unchanged, but the pylon 28b is disposed at an angle θ that is the same size but opposite sign as the angle α of the proximal mounting assembly 26 a.

FIG. 5 shows proximal mounting assembly 26b and distal mounting assembly 40b mounted to form nacelle 15b, which nacelle 15b is mounted to right wing 14 b. As shown, the distal prongs also extend generally perpendicular to the ground 5 when installed.

First, the engines 16a, 16b are disposed in the same orientation regardless of their location on the left or right wing.

Each flap can be adjusted according to the local aerodynamic conditions of each wing without the need to adjust the rest of the engine or nacelle, resulting in a potential further improvement in aerodynamics.

Fig. 8 shows alternative configurations for engine mounting, in which a pod nacelle is positioned over the wing.

Fig. 8 shows a right wing 114b of an aircraft having a dihedral, wherein the engine is mounted above the wing 114b as in the previous embodiment , but the engine mounting is different.

The aircraft includes an engine 116b housed within a nacelle 115b, which is mounted at a mounting location 124 provided at an upper surface 118b of the wing 114b as shown, a proximal mounting assembly 126b is provided, the proximal mounting assembly 126b being similar to the mounting assembly 26b but disposed inverted relative to the arrangement 26b, in other words, the mounting assembly 126b is mounted proximate the upper surface 118b of the wing 114b and includes a pylon 128b with a proximal end of the pylon 128b mounted to the wing 114b at the mounting location, coupling a distal/radially inner end of the pylon 128b to a partially annular coupling member 130b, which is similar to the coupling member of the th embodiment.

Fig. 9 shows a front view of an aircraft 210 including a fourth engine configuration. As shown, aircraft 210 also includes a fuselage 212, a left wing 214a, and a right wing 214 b. Engines 216a, 216b are also provided. In this case, however, the engines 216a, 216b are mounted to the sides of the fuselage 212, rather than to the wings 214a, 214 b.

As shown, engines 216a, 216b are mounted to respective pylons 228a, 228b each of which projects from a side surface of the fuselage, but is oriented at an angle of inclination of about 10 away from horizontal plane 260 (defining axis in this example). Each engine 216a, 216b includes a proximal mounting assembly 226a, 226b positioned adjacent aircraft fuselage 212. proximal mounting assembly 226b is similar to mounting assembly 26b, but is oriented at 90 relative to arrangement 26 b. in other words, mounting assembly 226b is mounted proximate the side surface of the fuselage and includes pylons 228a, 228b, with proximal ends of pylons 228a, 228b mounted to fuselage 212 at mounting location 224, which is located at aircraft tail 270, adjacent the rear of the aircraft.distal ends of pylons 228a, 228b define a bifurcation a, 246b coupled to a bifurcated partial annular coupling member 230b, which is similar to the coupling member of the embodiment.

In accordance with the above arrangement, further optimization can be achieved in the existing design, the nacelle aerodynamic design is a compromise between the port and starboard engines, as the interaction between the nacelle and the ground and between the nacelle and the wings occurs at different locations on the port and starboard engines.

Unless mutually exclusive, any feature may be used alone or in combination with any other feature, and the disclosure extends to and includes all combinations and subcombinations of the or more features described herein.

For example, a wing may have a dihedral (sloping towards the ground from root to tip). The engine may be of any suitable bypass type, such as direct drive or geared drive.