CN114802775A

CN114802775A - Aircraft engine nacelle and aircraft engine

Info

Publication number: CN114802775A
Application number: CN202110118350.8A
Authority: CN
Inventors: 刘钊; 徐燕; 丁晨
Original assignee: AECC Commercial Aircraft Engine Co Ltd
Current assignee: AECC Commercial Aircraft Engine Co Ltd
Priority date: 2021-01-28
Filing date: 2021-01-28
Publication date: 2022-07-29

Abstract

The invention discloses an aircraft engine nacelle and an aircraft engine. The aeroengine nacelle includes intake duct, fan machine casket and strengthening rib, and the intake duct includes the lip, and the fan machine casket is connected in the axial rear side of intake duct, and the strengthening rib sets up on the outer wall of intake duct and fan machine casket and extends along the axial, and the inner chamber of strengthening rib forms the air feed channel who supplies the steam flow, and steam flows to the lip through air feed channel. The aero-engine nacelle of the invention forms an air supply channel by utilizing the air inlet and the inner cavity of the reinforcing rib arranged on the outer wall of the fan case, so as to prevent the lip surface from being frozen. And parts such as an air supply pipeline specially used for supplying hot air are omitted, so that the maintainability of the nacelle is improved.

Description

Aircraft engine nacelle and aircraft engine

Technical Field

The invention relates to an aircraft engine nacelle and an aircraft engine.

Background

The lip area of the nacelle of the aircraft engine is prone to icing, and the icing in the lip area may change the cross-sectional shape of the air inlet, causing the aerodynamic profile of the air inlet to be damaged, thereby resulting in a reduction in the thrust of the aircraft engine. The ice layer accumulated in the air inlet channel can fall off, and the sucked air enters the engine and impacts the fan blades in a high-speed state to mechanically damage the air compressor, and even cause flight accidents. Therefore, in order to ensure the flight safety of the airplane, measures are required to prevent the lip surface from being frozen.

It is common practice to prevent icing in the lip area by drawing hot air from the engine to heat the lip area. In this solution, an air supply line extending from the engine to the lip needs to be specially provided to channel the hot air to the lip. This air supply line requires a separate air supply pipe and associated connections and supports, and therefore adds to the weight of the nacelle of the aircraft engine. And because the part is more, difficult assembly and follow-up also good maintenance.

Disclosure of Invention

The invention provides an aircraft engine nacelle and an aircraft engine, which are used for preventing the icing of a lip surface.

In a first aspect the present invention provides an aircraft engine nacelle comprising:

an inlet channel comprising a lip;

the fan casing is connected to the axial rear side of the air inlet; and

the strengthening rib sets up on the outer wall of intake duct and fan machine casket and along axial extension, and the inner chamber of strengthening rib forms the air feed channel that supplies the steam flow, and steam flows to the lip through air feed channel.

In some embodiments, the stiffener includes an inner cavity that is circumferentially closed to form the air supply channel, and connection ends that are disposed on both sides of the inner cavity to connect with the outer wall.

In some embodiments, the reinforcing rib comprises an inner cavity and a connecting end, the inner cavity is provided with an opening facing one side of the outer wall in the circumferential direction, the connecting end is arranged on two sides of the opening to be connected with the outer wall, and the inner cavity and the outer wall jointly enclose to form the air supply channel.

In some embodiments, the cross-sectional shape of the lumen includes circular, square, rectangular, trapezoidal, or semi-circular.

In some embodiments, the cross-sectional shape of the lumen is the same at different locations in the axial direction; alternatively, the cross-sectional shape of the lumen may be different at different positions in the axial direction.

In some embodiments, the reinforcing ribs include a first reinforcing rib provided on an outer wall of the air inlet duct and a second reinforcing rib provided on an outer wall of the fan case, and the first reinforcing rib and the second reinforcing rib are connected.

In some embodiments, the reinforcing bar further comprises a coupling joint, wherein the coupling joint is configured to couple the first reinforcing bar and the second reinforcing bar; alternatively, the coupling sub is configured to be provided at a free end of the first reinforcing bar and/or a free end of the second reinforcing bar.

In some embodiments, the reinforcing bars comprise a metallic material or a composite material.

In a second aspect, the invention provides an aircraft engine comprising an aircraft engine nacelle as described above.

Based on the aspects provided by the invention, the aircraft engine nacelle comprises an air inlet, a fan case and a reinforcing rib, wherein the air inlet comprises a lip, the fan case is connected to the axial rear side of the air inlet, the reinforcing rib is arranged on the outer walls of the air inlet and the fan case and extends along the axial direction, an inner cavity of the reinforcing rib forms an air supply channel for hot air to flow, and the hot air flows to the lip through the air supply channel. The aero-engine nacelle of the invention forms an air supply channel by utilizing the air inlet and the inner cavity of the reinforcing rib arranged on the outer wall of the fan case, so as to prevent the lip surface from being frozen. And parts such as an air supply pipeline specially used for supplying hot air are omitted, so that the maintainability of the nacelle is improved.

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

Drawings

The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the invention and together with the description serve to explain the invention without limiting the invention. In the drawings:

FIG. 1 is a schematic cross-sectional view of a related art nacelle for an aircraft engine;

FIG. 2 is a schematic perspective view of a related art nacelle for an aircraft engine;

FIG. 3 is a schematic perspective view of an aircraft engine nacelle according to an embodiment of the invention;

fig. 4 is a partially enlarged view illustrating a coupling portion of the coupling sub and the first reinforcing bars of fig. 3;

FIG. 5 is a schematic cross-sectional view of a reinforcing bar according to an embodiment of the present invention;

fig. 6 is a schematic cross-sectional view of a reinforcing bar according to another embodiment of the present invention.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of 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. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, 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 present invention unless specifically stated otherwise. Meanwhile, it should be understood that the sizes of the respective portions shown in the drawings are not drawn in an actual proportional relationship for the convenience of description. Techniques, methods, and apparatus known to those of ordinary skill in the relevant art may not be discussed in detail, but are intended to be part of the specification where appropriate. In all examples shown and discussed herein, any particular value should be construed as exemplary only and not as limiting. Thus, other examples of the exemplary embodiments may have different values. It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, further discussion thereof is not required in subsequent figures.

Spatially relative terms, such as "above … …," "above … …," "above … … surface," "above," and the like, may be used herein for ease of description to describe one device or feature's spatial relationship to another device or feature as illustrated in the figures. It will be understood that the 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 a device in the figures is turned over, devices described as "above" or "on" other devices or configurations would then be oriented "below" or "under" the other devices or configurations. Thus, the exemplary term "above … …" can include both an orientation of "above … …" and "below … …". The device may be otherwise variously positioned and the spatially relative descriptors used herein interpreted accordingly.

As shown in fig. 1 and 2, in some embodiments, an aircraft engine nacelle includes an air intake 101, a fan case 104, and an air supply duct 105. The air inlet 101 includes a lip 102, a front bulkhead 106, a rear bulkhead 107, an inner wall plate, and an outer wall plate 103. The air supply line 105 needs to pass through the fan case 104 and the air inlet 101 to deliver hot air to the lip 102 to prevent ice from forming on the surface of the lip 102. But also to melt ice from the surface of the lip 102.

As shown in fig. 2, in some embodiments, ribs 201 are provided on the outer surface of the outer wall plate 103 and the fan case 104 of the air inlet 101 to improve the strength and rigidity of the wall plate.

In view of this, with reference to fig. 1 and 3, an embodiment of the present invention provides an aircraft engine nacelle. The nacelle of the aircraft engine comprises an air inlet 101, a fan casing 104 and reinforcing ribs. The inlet 101 comprises a lip 102. The fan case 104 is connected to the axial rear side of the intake duct 101. The strengthening rib sets up and extends along the axial on the outer wall of intake duct 101 and fan machine case 104, and the inner chamber of strengthening rib forms the air feed channel that supplies steam flow, and steam flows to the lip through air feed channel.

Compared with the embodiment shown in fig. 1 and 2, the air supply channel is formed by the inner cavity of the reinforcing rib arranged on the outer wall of the air inlet channel 101 and the fan casing 104, and an air supply pipeline specially used for conveying hot air does not need to be additionally arranged, so that the structure of the nacelle is simplified, and the weight of the nacelle is reduced. Furthermore, in the embodiment shown in fig. 1 and 2, the air supply pipeline has large parts such as connecting brackets, joints and the like, and the maintenance performance is poor, while the nacelle in the embodiment shown in fig. 3 omits the parts such as the joints and the like, so that the maintenance performance of the nacelle is improved.

Referring to fig. 3, in some embodiments, the reinforcing ribs include a first reinforcing rib 301 disposed on an outer wall of the fan case and a second reinforcing rib 302 disposed on an outer wall of the air inlet duct. The first reinforcing bead 301 and the second reinforcing bead 302 are connected and communicated with each other. That is, in this embodiment, the first rib 301 extending in the axial direction is provided on the outer wall of the fan case, the second rib 302 is provided on the outer wall of the air inlet, and the first rib 301 and the second rib 302 are provided independently and connected to each other. The hot air circulates from the first bead 301 to the second bead 302 and is output to the lip.

In order to prevent the joint between the first reinforcing bead 301 and the second reinforcing bead 302 from being airtight, a coupling joint is provided between the first reinforcing bead 301 and the second reinforcing bead 302. The butt joint or lap joint mode can be adopted between the connecting joint and the reinforcing rib, and sealing is mainly guaranteed.

In other embodiments, not shown in the figures, the outer wall of the fan casing and the outer wall of the air inlet duct are provided with ribs integrally arranged in the axial direction.

In some embodiments, the nacelle further comprises a connection joint. The connection joint is configured to be provided to an end portion of the reinforcing bead. Referring to fig. 3, in some embodiments, the nacelle includes a first connector tab 303 and a second connector tab 304, wherein the first connector tab 303 is disposed at a free end of the first stiffener 301 and the second connector tab 304 is disposed at a free end of the second stiffener 302.

Referring to fig. 4, in this embodiment, the first reinforcing bead 301 has a trapezoidal sectional shape. The end surface of the first coupling boss 303 coupled to the first reinforcing bead 301 is also trapezoidal, and the end surface of the first coupling boss 303 remote from the end of the first reinforcing bead 301 is circular. Similarly, the end surface of the second connector 304 that is away from the end of the second stiffener 302 is also rounded, and the rounded end surface is also configured to facilitate connection with other pipes.

In other embodiments not shown in the drawings, the cross-sectional shape of the end face of the coupling joint near one end of the reinforcing bar is the same as the reinforcing bar, and the cross-sectional shape of the end face of the coupling joint far from one end of the reinforcing bar is circular to facilitate connection with other pipes.

In the above embodiment, the inner cavities of the reinforcing ribs form gas supply channels for the flow of hot gas. In some embodiments, the internal cavity of the stiffener itself forms a gas supply channel for the flow of hot gas. In other embodiments, the inner cavity of the stiffener and the outer wall plate of the air inlet duct and the fan casing together form an air supply channel for hot air to flow.

In some embodiments, referring to fig. 5, the stiffener includes an internal cavity and a connecting end. The inner cavity has an opening facing the outer wall in the circumferential direction. The connecting end is arranged on two sides of the opening to be connected with the outer wall, and the inner cavity and the outer wall jointly enclose and close to form an air supply channel.

In this embodiment, the first reinforcing bead 301 and the second reinforcing bead 302 have the same structure, and as shown in fig. 5, the structure of the first reinforcing bead 301 will be described as an example. The first reinforcing rib 301 includes an inner cavity 3011 and a first connection end 3012 and a second connection end 3013 connected to two sides of the inner cavity 3011. The first connection end 3012 and the second connection end 3013 are used to connect to the fan casing 104. The inner cavity 3011 has an opening facing the fan casing 104, and the inner cavity 3011 and the fan casing 104 together enclose to form an air supply channel.

In this embodiment, the cavity 3011 is trapezoidal in cross-section. In other embodiments not shown in the drawings, the cross-section of the inner cavity may also be circular, square, rectangular or semicircular, without limitation.

In other embodiments, as shown with reference to fig. 6, the stiffener includes an inner cavity that is circumferentially closed to form the air supply channel, and connection ends that are disposed on both sides of the inner cavity to connect with the outer wall. As shown in fig. 6, the structure of the first rib 601 will be described as an example. The first reinforcing rib 601 includes an inner cavity 6011 and a first connection end 6012 and a second connection end 6013 connected to both sides of the inner cavity 6011, respectively. Wherein the first connection end 6012 and the second connection end 6013 are used for connecting with the fan case 104. The interior cavity 6011 is itself a closed cavity that may form a gas supply channel. This inner chamber 6011 is the closed chamber, therefore the hot-air circulates in the closed chamber, and then plays the effect of keeping apart steam and link, and then effectively avoids being connected the problem of failing because of the strengthening rib of high temperature bleed and fan machine casket 104. Comparing the structure of the first reinforcing bead of the two embodiments of fig. 5 and 6, the first reinforcing bead 601 of the embodiment of fig. 6 corresponds to the addition of a partition plate between both sidewalls of the trapezoidal section, which serves to insulate hot air, as compared with the structure of the first reinforcing bead 301 of the embodiment of fig. 5.

In some embodiments, the cross-sectional shape of the lumen includes circular, square, rectangular, trapezoidal, or semi-circular. The cross section of the inner cavity of the reinforcing rib is not limited in the embodiment of the invention, and the reinforcing rib can be enclosed to form an air supply channel for flowing of hot air.

In some embodiments, the cross-sectional shape of the lumen is the same at different locations in the axial direction. In other embodiments, the cross-sectional shape of the lumen is different at different locations in the axial direction. That is to say the reinforcing bars are in the form of a varying section.

The structure of a nacelle for an aircraft engine according to an embodiment of the invention will now be described in detail with reference to figures 3 to 6.

Referring to fig. 1 and 3, an aircraft engine nacelle according to an embodiment of the invention includes an air intake 101 and a fan case 104. When the reinforcing ribs are designed, the outer wall plates of the air inlet 101 and the fan case 104 adopt a hat-shaped reinforcing rib mode, the hat-shaped reinforcing rib comprises a first reinforcing rib 301 positioned on the fan case 104 and a second reinforcing rib 302 positioned on the air inlet 101, and the positions of the second reinforcing rib 302 on the air inlet 101 and the first reinforcing rib 301 on the fan case 104 are ensured to be consistent and are connected by a connecting joint (not shown in the figure). Referring to fig. 5, the trapezoidal gap formed between the cap stiffener and the outer wall panel guides the flow of hot air to the lip region. Meanwhile, as shown in fig. 3, it is necessary to provide a first coupling joint 303 and a second coupling joint 304 at the inlet and outlet positions of the cap type reinforcing bars, respectively.

To ameliorate this problem, the first stiffener 601 shown in figure 6 can be used, and heat in the hat stiffener can cause the connection between the stiffener and the outer wall plate to fail.

In this embodiment, the connection joint may be a metal or a non-metal member, and may be butted or butted.

The connection between the first reinforcing rib 301 and the fan case 104 may be an adhesive or a mechanical connection using a fastener. Similarly, the connection between the second reinforcing rib 302 and the air inlet channel 101 may be an adhesive or a mechanical connection using a fastener.

The first reinforcing bead 301 may be made of a high-temperature-resistant metal material or a composite material. The second reinforcing ribs 302 may be made of a high temperature resistant metal material or a composite material.

The cap-shaped reinforcing rib can change the cross section form, and is a closed space, such as a round, square, rectangular or semicircular shape. Or can be connected with the outer wall plate and then can be enclosed together to form a closed space.

The first connection joint 303 and the second connection joint 304 may be metal or non-metal members.

The first and second connection joints 303 and 304 may be butted or butted against the cap type reinforcing bars as long as the sealing condition can be secured.

Finally, it should be noted that: the above examples are only intended to illustrate the technical solution of the present invention and not to limit it; although the present invention has been described in detail with reference to preferred embodiments, those skilled in the art will understand that: modifications to the specific embodiments of the invention or equivalent substitutions for parts of the technical features may be made; without departing from the spirit of the present invention, it is intended to cover all aspects of the invention as defined by the appended claims.

Claims

1. An aircraft engine nacelle, comprising:

an inlet channel comprising a lip;

the fan casing is connected to the axial rear side of the air inlet; and

the strengthening rib, set up in the intake duct with just extend along the axial on the outer wall of fan machine casket, just the inner chamber of strengthening rib forms the air feed channel that supplies hot gas flow, and hot gas passes through air feed channel flows extremely the lip.

2. The nacelle according to claim 1, wherein the reinforcing ribs include an inner cavity that is closed in the circumferential direction to form the air supply passage, and connecting ends that are provided on both sides of the inner cavity to connect with the outer wall.

3. The nacelle according to claim 1, wherein the reinforcing ribs include an inner cavity having an opening in a circumferential direction toward one side of the outer wall, and connecting ends provided on both sides of the opening to connect with the outer wall, the inner cavity and the outer wall together enclosing the air supply passage.

4. The nacelle according to claim 1, wherein the cross-sectional shape of the interior cavity comprises a circle, square, rectangle, trapezoid, or semicircle.

5. The nacelle according to claim 1, wherein the cross-sectional shape of the inner cavity is the same at different positions in the axial direction; alternatively, the cross-sectional shape of the lumen may be different at different positions in the axial direction.

6. The nacelle according to any one of claims 1 to 5, wherein the reinforcing ribs include a first reinforcing rib provided on an outer wall of the air inlet duct and a second reinforcing rib provided on an outer wall of the fan case, and the first reinforcing rib and the second reinforcing rib are connected.

7. The nacelle according to claim 6, wherein the reinforcing ribs further comprise a connection joint, wherein the connection joint is configured to connect the first reinforcing rib and the second reinforcing rib; alternatively, the coupling sub is configured to be provided at a free end of the first reinforcing bar and/or a free end of the second reinforcing bar.

8. The nacelle according to claim 1, wherein the reinforcing ribs comprise a metallic material or a composite material.

9. An aircraft engine, characterized in that it comprises a nacelle according to any one of claims 1 to 8.