CN114790943A - Air inlet duct of aircraft engine nacelle and aircraft engine nacelle - Google Patents

Abstract

The invention discloses an air intake channel of an aero-engine nacelle and an aero-engine nacelle. The air inlet of the aero-engine nacelle includes an inner wall plate and a butt ring, the inner surface of the inner wall plate forms a gas flow channel surface and the outer surface includes a first mating surface, the butt ring is used to connect the inner wall plate and the fan case, and the butt ring includes The second mating surface, the second mating surface and the first mating surface are mutually attached and connected, and both the first mating surface and the second mating surface are single curved surfaces. The mating surface of the butt ring of the air inlet and the inner wall plate adopts a single curved surface, which is convenient for the machining and manufacture of the butt ring. Moreover, when the inner wall plate is horizontally assembled and installed along the axis of the engine, the butt ring can be installed from the rear end of the inner wall plate to the theoretical position, which minimizes the assembly and installation path.

Description

Air intakes and aero-engine nacelles

technical field

The invention relates to an air intake channel of an aero-engine nacelle and an aero-engine nacelle.

Background technique

The civil turbofan nacelle system is usually composed of an intake and exhaust system, a fan cover and a thrust reverser, including an air intake, a fan casing, a thrust reverser, a nozzle and a central cone. Functionally, the air inlet mainly rectifies the external air flow, and at the same time, through the lip and inner wall plate structure of the air inlet on the runner surface, the external air flow is rectified into the engine fan blade according to the established runner. Structurally, the air intake duct and the fan casing are installed and connected through a butt ring, and at the same time, the butt ring is connected with the inner wall plate structure on the flow channel surface.

SUMMARY OF THE INVENTION

The invention provides an air intake channel of an aero-engine nacelle and an aero-engine nacelle, so as to reduce the processing difficulty of the butt ring.

A first aspect of the present invention provides an air intake duct for an aero-engine nacelle, comprising:

an inner wall plate, the inner surface forms a gas flow channel surface and the outer surface includes a first mating surface; and

The butt ring is used to connect the inner wall plate and the fan casing, and the butt ring includes a second mating surface, the second mating surface and the first mating surface are mutually attached and connected, and both the first mating surface and the second mating surface are single curved surfaces .

In some embodiments, the single curved surface is centered on the centerline of the aero-engine.

In some embodiments, the single curved surface includes a cylindrical or conical surface.

In some embodiments, the inner wall panel includes a front panel, a back panel and a honeycomb, the honeycomb is sandwiched between the panel and the back panel, the back panel forms an outer surface of the inner wall panel, the back panel includes a back panel main body section and a back panel connection section, and the back panel The plate connecting section is located at the axial rear end of the main body section of the back plate and forms a first mating surface. The honeycomb includes a main body section of honeycomb corresponding to the main section of the back plate and a connecting section of honeycomb corresponding to the connecting section of the back plate. Including a connecting piece, the connecting piece connects the butt ring and the inner wall plate.

In some embodiments, the connector passes sequentially through the butt ring, the back panel connection segment, the honeycomb connection segment, and the faceplate.

In some embodiments, the cell density of the cellular connection segment is greater than the cellular density of the cellular body segment.

In some embodiments, the honeycomb connection section has the same honeycomb density as the honeycomb body section, and the nacelle air intake further includes a countersunk bushing that penetrates into the inner wall panel from one side of the panel and wraps around the connection outside of the piece.

In some embodiments, the second mating surface is a clearance fit with the first mating surface.

A second aspect of the present invention provides an aero-engine nacelle, comprising the above-mentioned air intake.

The air intake channel of the aero-engine nacelle provided by the present invention includes an inner wall plate and a butt ring, the inner surface of the inner wall plate forms a gas flow channel surface and the outer surface includes a first mating surface, and the butt ring is used to connect the inner wall plate and the fan case. , and the butt ring includes a second matching surface, the second matching surface and the first matching surface are mutually attached and connected, and both the first matching surface and the second matching surface are single curved surfaces. The mating surface of the butt ring of the air inlet and the inner wall plate adopts a single curved surface, which is convenient for the machining and manufacture of the butt ring. Moreover, when the inner wall plate is horizontally assembled and installed along the engine axis, the butt ring can be installed from the rear end of the inner wall plate to the theoretical position, which shortens the assembly and installation path to the greatest extent.

Other features and advantages of the present invention will become apparent from the following detailed description of exemplary embodiments of the present invention with reference to the accompanying drawings.

Description of drawings

The accompanying drawings described herein are used to provide a further understanding of the present invention and constitute a part of the present application. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the attached image:

Fig. 1 is the structural schematic diagram of aero-engine nacelle;

Figure 2 is a schematic diagram of the cross-sectional structure of the air inlet;

Figure 3 is a perspective view of the inner wall plate and the butt ring in Figure 2;

Fig. 4 is the structural diagram of the inner wall plate and the butt ring in Fig. 2;

Fig. 5 is a partial enlarged view of the inner wall plate and the butt ring in Fig. 4;

Fig. 6 is the installation diagram of the butt ring and the inner wall plate in Fig. 2;

7 is a schematic structural diagram of a butt ring and an inner wall plate according to an embodiment of the present invention;

Fig. 8 is a partial enlarged view of the connection portion between the butt ring and the inner wall plate in Fig. 7;

FIG. 9 is an installation structural diagram of an air intake duct and a fan casing according to an embodiment of the present invention;

FIG. 10 is a schematic diagram of an installation section of an air intake duct and a fan casing and a step difference adjustment and compensation design method according to an embodiment of the present invention;

11 is a schematic diagram of the connection between the butt ring and the inner wall plate according to the embodiment of the present invention;

12 is a schematic diagram of the connection between the butt ring of the intake port and the inner wall plate according to another embodiment of the present invention.

Detailed ways

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. The following description of at least one exemplary embodiment is merely illustrative in nature and is in no way intended to limit the invention, its application, or uses. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

The relative arrangement of the components and steps, the numerical expressions and numerical values set forth in these embodiments do not limit the scope of the invention unless specifically stated otherwise. Meanwhile, it should be understood that, for the convenience of description, the dimensions of various parts shown in the accompanying drawings are not drawn in an actual proportional relationship. Techniques, methods, and apparatus known to those of ordinary skill in the relevant art may not be discussed in detail, but where appropriate, techniques, methods, and apparatus should be considered part of the authorized description. In all examples shown and discussed herein, any specific value should be construed as illustrative only and not as limiting. Accordingly, other examples of exemplary embodiments may have different values. It should be noted that like numerals and letters refer to like items in the following figures, so once an item is defined in one figure, it does not require further discussion in subsequent figures.

For ease of description, spatially relative terms, such as "on", "over", "on the surface", "above", etc., may be used herein to describe what is shown in the figures. The spatial positional relationship of one device or feature shown to other devices or features. It should be understood that spatially relative terms are intended to encompass different orientations of the device in use or operation in addition to the orientation depicted in the figures. For example, if the device in the figures is turned over, elements described as "above" or "over" other devices or features would then be oriented "below" or "over" the other devices or features under other devices or constructions". Thus, the exemplary term "above" can encompass both an orientation of "above" and "below." The device may also be positioned in other different ways, and the spatially relative descriptions used herein interpreted accordingly.

As shown in FIG. 1 , an aero-engine nacelle according to some embodiments of the present invention includes an air intake 1 , a fan casing 2 , a thrust reverser 3 , a nozzle and a central cone 4 .

As shown in FIG. 2 , in some embodiments, the air inlet 1 includes a front bulkhead 11 , a rear bulkhead 12 , an outer wall panel 13 , an inner wall panel 14 , a butt ring 15 and a lip 16 . The lip 16 is connected to the front side of the front partition frame 11, the front and rear ends of the outer wall plate 13 are respectively connected to the front partition frame 11 and the rear partition frame 12, and the front and rear ends of the inner wall plate 14 are respectively connected to the front partition frame 11 and the rear partition frame 11. The partition frames 12 are connected, wherein the inner wall plate 14 is arranged on the radially inner side, and the outer wall plate 13 is arranged on the radially outer side. The butt ring 15 is used to connect the inner wall plate 14 and the fan casing 2 .

As shown in FIG. 3 , in some embodiments, the inner wall plate 14 is arranged in an annular shape, and the inner surface of the inner wall plate 14 forms a gas flow channel surface. As shown in FIG. 4 , the outer surface of the inner wall plate 14 is connected to the butt ring 15 .

The inner wall plate 14 has a noise reduction function of a sound lining to suppress the noise of the fan blades. In order to maximize the effective noise reduction area of the acoustic lining of the inner wall panel 14, an integral seamless acoustic lining structure is usually adopted, that is, the inner wall panel 14 is a circumferentially integral seamless closed structure. Correspondingly, since one end of the butt ring 15 is connected with the fan casing 2 , the other end is connected with the inner wall plate 14 . Fan casing 2 is also known as fan containing casing. Under the condition of FBO blade falling off load, the debris is not allowed to fly out of the casing and damage the peripheral accessories. Therefore, the axial structure is designed to be continuous and there is no weak area. Generally, the annular integral type is used. Sewing casing structure. Correspondingly, the docking ring 15, as a structure directly connected to the fan casing 2, adopts a 360° integral annular structure in consideration of the FBO load condition. Similarly, the inner wall panel 14 also adopts an integral seamless structure. As shown in FIG. 4 and FIG. 5 , in the nested connection area of the two large-sized integral annular structures, the mating surface of the butt ring 15 and the inner wall plate 14 is parallel to the flow channel surface. In this way, since the flow channel surface is a hyperbolic surface, the butt ring 15 also needs to use a hyperbolic surface, which will increase the manufacturing and processing cost of the butt ring, increase the difficulty of the process, and reduce the processing efficiency at the same time. Secondly, due to the characteristics of the given flow channel surface of the hyperbolic profile, the profile at the butt ring is usually flared, that is, the front end of the flow channel surface at the connection between the butt ring 15 and the inner wall plate 14 is small at the front end and large at the rear end. This determines the assembly relationship between the two here, as shown in Figure 6, that is, the butt ring 15 can only penetrate the entire inner wall plate from the front edge until it reaches the installation position, the assembly operation is difficult, the assembly stroke is long, and the two large sizes during the installation process. In the process of fitting the parts, it is easy to cause scratches and even impact damage.

As shown in FIG. 5, in some embodiments, the inner wall panel 14 includes a front panel 14a, a back panel 14b, and a honeycomb 14c. In one embodiment, the front panel 14a and the back panel 14b are typically carbon fiber composite materials. In addition, the panel 14a has the geometric features of noise reduction perforation, and the honeycomb 14c of the sandwich layer is a Nomex aramid paper honeycomb, and the above three are formed and bonded by co-bonding or secondary bonding. In another embodiment, the front panel 14a and the back panel 14b are made of an aluminum alloy sheet structure and are glued and solidified with the honeycomb 14c. The structures and materials of the inner wall panels listed above are only two examples, and the actual implementation includes, but is not limited to, the above-mentioned materials and processes, and may also be a combination of the above-mentioned two materials.

In the embodiment in which the front panel 14a and the back panel 14b are made of carbon fiber composite materials, where the inner wall panel 14 and the butt ring 15 are assembled, the carbon fiber layer of the back panel 14b is partially thickened and a glass cloth sacrificial layer is added on the side close to the butt ring 15 The glass cloth layer can be polished and repaired to facilitate the assembly of the inner wall plate and the butt ring. When coordinating assembly with the butt ring 15 , the butt ring is partially or entirely repaired to achieve the purpose of adjusting the assembly level difference between the entire air intake duct 1 and the fan casing 5 . Similarly, in the embodiment in which the front panel 14a and the back panel 14b adopt the aluminum alloy sheet structure, where the inner wall panel 14 and the butt ring 15 are assembled, the back panel 14b may need to be thickened by milling or machining to achieve structural thickening and to reserve subsequent assembly. Machining or grinding process allowance.

The butt ring 15 is an aluminum alloy structure added by an integral ring forging machine. Considering the fire protection requirements, the design is generally wrapped with a fireproof blanket. Fire blankets are not required when the area where the butt ring is located is a non-fire zone.

In view of the above-mentioned difficulty in manufacturing and processing the butt ring, in order to reduce the manufacturing difficulty of the butt ring, an embodiment of the present invention proposes an aero-engine nacelle.

7 and 8, the air intake of the aero-engine nacelle of some embodiments includes an inner wall panel 17 and a butt ring 18. The inner surface of the inner wall plate 17 forms a gas flow channel surface, and the outer surface of the inner wall plate 17 includes a first matching surface. The butt ring 18 is used for connecting the inner wall plate 17 and the fan casing 2 , and the butt ring 18 includes a second mating surface. The second matching surface and the first matching surface are attached and connected to each other, and both the first matching surface and the second matching surface are single curved surfaces.

In some embodiments, the mating surface of the butt ring 18 and the inner wall plate 17 of the air inlet adopts a single curved surface, which is convenient for machining and manufacture of the butt ring. Moreover, when the inner wall plate 17 is horizontally assembled and installed along the engine axis, the butt ring 18 can be installed from the rear end of the inner wall plate 17 to the theoretical position, and the assembly and installation path can be shortened to the maximum extent. In the embodiment shown in FIG. 6 , the butt ring is installed from the front end of the inner wall plate, and its installation path is long, and the butt ring needs to be fine-tuned several times to avoid interference damage with the inner wall plate back plate during the installation process.

In some embodiments, the single curved surface is centered on the centerline of the aero-engine. In this way, the first mating surface and the second mating surface are coaxially arranged, which is convenient for assembly.

In some embodiments, the single curved surface includes a cylindrical surface. By adopting the butt ring structure of the cylindrical rotary structure, the manufacturing cost is reduced, the processing difficulty is reduced, and the processing cycle is shortened. In other embodiments, the single curved surface may also be a conical surface.

As shown in FIG. 8 , the outer surface of the inner wall plate 17 in this embodiment includes a first mating surface and a main wall surface disposed on the axial front side of the first mating surface, and the main wall surface is parallel to the flow channel surface. That is to say, the inner wall plate 17 of this embodiment is divided into two sections in the axial direction. Non-smooth connections between mating faces.

In some embodiments, referring to FIG. 10 , the second mating surface is a clearance fit with the first mating surface. That is to say, a certain assembly gap D is designed and reserved between the assembly and mating surfaces of the butt ring 18 and the inner wall plate 17 to compensate for the manufacturing deviation and assembly error of the two large-sized annular structures. Refer to FIG. 9 and FIG. 10 at the same time. , the assembly gap D is also used to adjust the axial position of the butt ring 18 of the entire intake duct 1 and the fan casing 2, so as to realize the control of the level difference of the flow passages after the installation of the intake duct 1 and the fan casing 2, so as to achieve Meet the design requirements of the aerodynamic smoothness of the runner surface.

In some embodiments, when the inner wall plate 17 on the flow channel surface is assembled with the butt ring 18 , if the butt ring 18 interferes with the inner wall plate 17 , the cylindrical mating surface is easy to repair and even the butt ring can be processed to complete assembly. And when there is a certain gap in the mating surface, a solid gasket with the same thickness and the same shape as a cylinder can be used to compensate for the assembly gap, and used in conjunction with the liquid gasket until the flow channel surface formed with the fan casing 2 after assembly The air flow gradient fully meets the aerodynamic requirements.

In some embodiments, referring to FIG. 8 , the inner wall panel 17 includes a front panel 17a, a back panel 17b and a honeycomb 17c, the honeycomb 17c is sandwiched between the panel 17a and the back panel 17b, the back panel 17b forms the outer surface of the inner panel 17, and the back panel 17b forms the outer surface of the inner panel 17. The plate 17b includes a main body section of the back plate and a connecting section of the back plate. The connecting section of the back plate is located at the axial rear end of the main body section of the back plate and forms a first mating surface. Corresponding to the honeycomb connecting section of the plate connecting section, the nacelle air inlet further includes a connecting piece 6 , and the connecting piece 6 connects the butt ring 18 and the inner wall plate 17 .

Specifically, the connecting member 6 is a high-lock bolt. In some embodiments, the connecting piece 6 penetrates the entire inner wall plate 17 to reach the pneumatic flow channel surface. Specifically, the connecting piece 6 passes through the butt ring 18 , the back plate connecting section, the honeycomb connecting section and the panel 17 a in sequence.

In order to enhance the strength of the cellular connection segments, in some embodiments, referring to FIG. 11 , the cellular density of the cellular connection segment 17d is greater than the cellular density of the cellular body segment 17e. Specifically, the honeycomb connecting section 17d adopts high-density aluminum honeycomb. In other embodiments, referring to FIG. 12 , the honeycomb density of the honeycomb connecting section is the same as that of the honeycomb main section, and the nacelle air inlet further includes a countersunk bushing 7 , which penetrates from one side of the panel 17a into the inner wall plate 17 and wrap it on the outside of the connecting piece 6 . In this embodiment, both the honeycomb connecting section and the honeycomb body section are made of common honeycomb materials, that is, the honeycomb of the entire inner wall panel is made of the same material, and the inner wall panel is buried only at the installation openings of the high-lock bolts connected to the butt ring 18 . Countersunk bushing 7 for through mechanical connection of high lock bolts.

In some embodiments not shown in the drawings, blind rivets may also be used to connect the butt ring 18 to the inner wall plate 17, and this connection method does not run through the entire inner wall plate. Of course, a combination of high-lock bolts and blind rivets penetrating the butt ring 18 and the inner wall plate 17 can also be used for hybrid connection.

Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and not to limit them; although the present invention has been described in detail with reference to the preferred embodiments, those of ordinary skill in the art should understand: The specific embodiments of the invention are modified or some technical features are equivalently replaced; without departing from the spirit of the technical solutions of the present invention, all of them should be included in the scope of the technical solutions claimed in the present invention.

Claims (9)

1. An air scoop for an aircraft engine nacelle, comprising:

an inner wall plate having an inner surface forming a gas flow passage surface and an outer surface including a first mating surface; and

the butt joint ring is used for connecting the inner wallboard and the fan casing and comprises a second matching surface, the second matching surface is mutually attached and connected with the first matching surface, and the first matching surface and the second matching surface are single curved surfaces.

2. The air scoop according to claim 1, wherein the single curved surface is centered on the centerline of the aircraft engine.

3. The air scoop according to claim 1, wherein the single curved surface comprises a cylindrical surface or a conical surface.

4. The air inlet duct of an aircraft engine nacelle according to claim 1, wherein the inner panel includes a face plate, a back plate, and a honeycomb, the honeycomb clamp is disposed between the face plate and the back plate, the back plate forms an outer surface of the inner panel, the back plate includes a back plate main body section and a back plate connecting section, the back plate connecting section is located at an axial rear end of the back plate main body section and forms the first mating surface, the honeycomb includes a honeycomb main body section corresponding to the back plate main body section and a honeycomb connecting section corresponding to the back plate connecting section, the nacelle air inlet duct further includes a connecting member, and the connecting member connects the docking ring and the inner panel.

5. The air inlet duct of an aircraft engine nacelle according to claim 4, wherein the connection piece passes through the docking ring, the back plate connection section, the honeycomb connection section, and the face plate in this order.

6. The air scoop according to claim 5, wherein the honeycomb density of the honeycomb connecting section is greater than the honeycomb density of the honeycomb main body section.

7. The air inlet duct for an aircraft engine nacelle according to claim 5, wherein the honeycomb density of the honeycomb connecting section is the same as that of the honeycomb main body section, and the nacelle air inlet duct further comprises a counter-sunk bush which penetrates into the inner wall plate from the panel side and wraps outside the connecting member.

8. The air scoop of an aircraft engine nacelle according to claim 1, wherein said second mating surface is a clearance fit with said first mating surface.

9. An aircraft engine nacelle, characterised in that it comprises an air inlet duct according to any one of claims 1 to 8.

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