CN212563479U

CN212563479U - Aeroengine, reverse thrust device and reverse thrust blade cascade thereof

Info

Publication number: CN212563479U
Application number: CN202021259513.1U
Authority: CN
Inventors: 张英杰; 曹骅; 杨颖�
Original assignee: AECC Commercial Aircraft Engine Co Ltd
Current assignee: AECC Commercial Aircraft Engine Co Ltd
Priority date: 2020-06-30
Filing date: 2020-06-30
Publication date: 2021-02-19
Anticipated expiration: 2030-06-30

Abstract

An object of the utility model is to provide a reverse thrust cascade can solve at least one problem that exists among the prior art. Another object of the present invention is to provide a thrust reverser, which has the aforementioned thrust reverser cascade. It is another object of the present invention to provide an aircraft engine having the aforementioned thrust reverser. The thrust reverser cascade for achieving the aforementioned object comprises a first member, a second member and a plurality of cascade units. The first component is provided with a first connecting part, the second component is provided with a second connecting part, each cascade unit body comprises at least one pair of connecting ribs and blade units vertically connected between the connecting ribs, and the two ends of each cascade unit body are respectively provided with a third connecting part and a fourth connecting part. The third connecting part can be connected with the first connecting part in a matching mode, and the fourth connecting part can be connected with the second connecting part in a matching mode, so that the blade cascade unit bodies are connected with the first component and the second component in a matching mode respectively to form a reverse thrust blade cascade.

Description

Aeroengine, reverse thrust device and reverse thrust blade cascade thereof

Technical Field

The utility model relates to an aeroengine, reverse thrust unit and reverse thrust cascade thereof.

Background

The thrust reverser can change the direction of the thrust of the engine and is used for shortening the sliding distance of the airplane during landing. The thrust reverser can help an airplane to land on a wet and slippery runway and can also be used as an emergency braking device when the airplane fails to take off, and the thrust reverser cascade is a key component for changing the exhaust flow direction of the engine.

The reverse thrust cascade is a porous grid type structure, in order to ensure the pneumatic profile of the cascade, the four sides of each grid of the cascade are required to have high-precision quality requirements in the design, so that each grid needs to be designed with a group of core moulds in the forming process, in addition, each group of core moulds can be divided into a plurality of small moulds in consideration of the demoulding problem, the integral cascade usually needs to be designed with hundreds or hundreds of moulds, and the integral cascade is difficult to manufacture as follows:

1) the number of the dies is large, the precision requirement is high, the die cost is high, and the integral blade cascade cost is high;

2) the mould equipment is complicated that mould quantity is many, and can't avoid having assembly stress in the assembling process, and unpredictable's assembly stress has unpredictable risk to cascade later stage shaping quality, and all kinds of defects can appear in the finished piece, lead to integral cascade yield low, and then lead to integral cascade with high costs, the scheduling problem is postponed to the progress.

There is a need for a thrust reversal cascade that solves at least one of the problems of the prior art.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide a reverse thrust cascade can solve at least one problem that exists among the prior art.

Another object of the present invention is to provide a thrust reverser, which has the aforementioned thrust reverser cascade.

It is another object of the present invention to provide an aircraft engine having the aforementioned thrust reverser.

To achieve the aforementioned object, a thrust reverser cascade comprises:

the first component provides a front end connecting edge of the thrust reversal blade cascade and is provided with a first connecting surface, and a first connecting part is arranged in the first connecting surface;

the second component is used for providing a rear end connecting edge of the thrust reversal blade cascade and is provided with a second connecting surface, and a second connecting part is arranged in the second connecting surface;

each blade grid unit body comprises at least one pair of connecting ribs and blade units vertically connected between the connecting ribs, and both ends of each blade grid unit body are respectively provided with a third connecting part and a fourth connecting part;

the third connecting part can be connected with the first connecting part in a matching mode, the fourth connecting part can be connected with the second connecting part in a matching mode, so that the blade cascade unit bodies are respectively connected with the first component and the second component in a matching mode to form the reverse thrust blade cascade, and the blade units in the two adjacent blade cascade unit bodies are provided with corresponding positions to form blades in the reverse thrust blade cascade in an assembling state.

In one or more embodiments, each of the cascade unit bodies includes a pair of connection ribs and a plurality of blade units connected between the pair of connection ribs.

In one or more embodiments, the plurality of cascade unit bodies include two side frame units and at least one middle frame unit, and the middle frame unit is located between the two side frame units in the assembled state;

wherein each of the frame units has reinforcing connecting ribs located on both sides of the thrust reverser cascade in the assembled state, the reinforcing connecting ribs having a thickness greater than the connecting ribs.

In one or more embodiments, the intermediate frame unit is a plurality of the intermediate frame units, and the plurality of the intermediate frame units have the same configuration.

In one or more embodiments, the blade units in the middle frame unit and the edge frame unit have the same length.

In one or more embodiments, the intermediate frame units are fixedly connected with each other.

In one or more embodiments, the first connection portion is a first groove portion provided in the first connection face, the second connection portion is a second groove portion provided in the second connection face, the third connection portion is a first lug extending inwardly at one end of the connection rib, and the fourth connection portion is a second lug extending inwardly at the other end of the connection rib;

the first lug is fixedly connected with the bottom wall of the first groove, and the second lug is fixedly connected with the bottom wall of the second groove.

In one or more embodiments, the first member has a first rim providing the leading connecting edge and a first connecting plate providing the first connecting face;

the second member has a second rim providing the rear end connecting edge and a second connecting plate providing the second connecting face.

The thrust reverser device for achieving the other aim comprises a thrust reversal blade cascade, a torque box and a blade cascade support ring, and is characterized in that the thrust reversal blade cascade is the thrust reversal blade cascade as described above;

the front end connecting edge is connected with the torque box, and the rear end connecting edge is connected with the cascade support ring.

An aircraft engine for achieving the aforementioned further object, comprising an engine nacelle, characterized in that a thrust reverser as described above is provided in the engine nacelle.

The utility model discloses an advance effect includes following one or combination:

1) the reverse thrust cascade adopts a split type manufacturing mode, the number of the molds needed by each cascade unit body 3 is small, the assembly is simple, the assembly stress in the assembly process is controllable, the split type structure cost rate is high, and the problems of high cost, delayed progress and the like of the traditional integral cascade can be solved.

2) In the cascade unit body in the reverse thrust cascade, the frame unit and the middle frame unit can adopt a set of core die, and all dies in the forming process can be shared because the middle frame has the same structure, thereby reducing the die cost.

Drawings

The above and other features, properties and advantages of the present invention will become more apparent from the following description of the embodiments with reference to the accompanying drawings, in which:

FIG. 1 shows an exploded schematic view of an embodiment of the present thrust reverser cascade;

FIG. 2 shows a perspective view of an embodiment of the present thrust reverser cascade;

FIG. 3 illustrates a schematic diagram of one embodiment of a leaf grid cell body;

FIG. 4 illustrates a perspective view of one embodiment of the first member.

Detailed Description

The following discloses many different embodiments or examples for implementing the subject technology described. Specific examples of components and arrangements are described below to simplify the present disclosure, but these are merely examples and are not intended to limit the scope of the present disclosure. For example, if a first feature is formed over or on a second feature described later in the specification, this may include embodiments in which the first and second features are formed in direct contact, and may also include embodiments in which additional features are formed between the first and second features, such that the first and second features may not be in direct contact. Additionally, reference numerals and/or letters may be repeated among the various examples throughout this disclosure. This repetition is for the purpose of simplicity and clarity and does not in itself dictate a relationship between the various embodiments and/or configurations discussed. Further, when a first element is described as being coupled or coupled to a second element, the description includes embodiments in which the first and second elements are directly coupled or coupled to each other, as well as embodiments in which one or more additional intervening elements are added to indirectly couple or couple the first and second elements to each other.

It should be noted that, where used, the following description of upper, lower, left, right, front, rear, top, bottom, positive, negative, clockwise, and counterclockwise are used for convenience only and do not imply any particular fixed orientation. In fact, they are used to reflect the relative position and/or orientation between the various parts of the object.

It should be noted that these and other figures are given by way of example only and are not drawn to scale, and should not be construed as limiting the scope of the invention as it is actually claimed. Further, the conversion methods in the different embodiments may be appropriately combined.

In order to solve the problems in at least one aspect of the background art, an aspect of the present invention provides a reverse thrust cascade. Fig. 1 is an exploded view of an embodiment of the thrust reverser cascade.

The reverse thrust blade cascade comprises a first member 1, a second member 2 and a plurality of blade cascade unit bodies 3.

The first component 1 provides a front connecting edge 10 of the thrust reverser cascade, which has a first connecting face 11, in which first connecting portion 110 is arranged in the first connecting face 11.

The second component 2 provides a rear connecting edge 20 of the thrust reverser cascade, which has a second connecting surface 21, in which second connecting surface 21 a second connecting portion 210 is arranged.

Each cascade unit body 3 includes a pair of connection ribs 30 and a blade unit 31 vertically connected between the connection ribs 30, and both ends of each unit body 3 have a third connection portion 33 and a fourth connection portion 34, respectively.

It is understood that the cascade unit 3 becomes a grid part in a reverse thrust cascade after being assembled, wherein the cascade unit 3 can be composed of a pair of connecting ribs 30 and a blade unit 31 vertically connected between the connecting ribs 30 as shown in the figure, and in some other embodiments, each cascade body can also include other numbers of connecting ribs 30, for example, in one embodiment, each cascade unit 3 includes 3 connecting ribs 30, and each two adjacent connecting ribs 30 become a pair of connecting ribs 30. In another embodiment, one of the cascade unit bodies 3 includes 3 connecting ribs 30, and the other cascade unit body 3 includes a pair of connecting ribs 30. Furthermore, in some other embodiments than those shown in the drawings, the number of blade units 31 arranged between the connecting ribs 30 may be other than that shown, and the actual number of blade units 31 depends on the actual application environment of the thrust reverser cascade.

With reference to fig. 1, the third connecting portion 33 can be connected to the first connecting portion 110 in a matching manner, and the fourth connecting portion 34 can be connected to the second connecting portion 210 in a matching manner, so that the blade cascade units 3 are respectively connected to the first member 1 and the second member 2 in a matching manner to form a reverse thrust blade cascade as shown in fig. 2. In the assembled state as shown in fig. 2, the blade units 31 in two adjacent cascade unit bodies 3 have corresponding positions so as to be aligned one by one in the assembled state to form blades in a reverse cascade. Considering the load transmission path of the blade cascade, the load is transmitted to the axial direction through the blades along the fiber and then transmitted to the connecting ends at the two sides along the axial direction, therefore, when the split design is carried out, considering the continuity of the blades and the axial load transmission, each frame is subjected to the split design at the connecting ribs 30, the load transmission path is not influenced, and the axial load is transmitted to the connecting ends through the front end connecting edges 10 and the rear end connecting edges 20 at the two sides.

The reverse thrust cascade is composed of a plurality of cascade unit bodies 3, a split type manufacturing mode is adopted, the number of dies required by each cascade unit body 3 is small, the assembly is simple, the assembly stress in the assembly process is controllable, the split type structure cost rate is high, and the problems that the traditional integral cascade is high in cost, the progress is delayed and the like can be solved.

Although one embodiment of the present thrust reversal cascade is described above, in other embodiments of the present thrust reversal cascade, the thrust reversal cascade may have more details in many respects than the above-described embodiments, and at least some of these details may have various variations. At least some of these details and variations are described below in several embodiments.

In one embodiment of the thrust reverser cascade, each cascade unit 3 is as shown in fig. 3 and comprises a pair of tie bars 30 and a plurality of blade units 31 connected between the pair of tie bars 30. By arranging a plurality of blade unit bodies 3 in a standard structure as shown in fig. 3, a set of core molds can be shared in the manufacturing process, and all molds in the molding process can be shared, thereby reducing the mold cost.

With continued reference to fig. 1, in an embodiment of the reverse cascade, the cascade units 3 include two border units 3a and at least one middle frame unit 3b, wherein the number of the middle frame units 3b is three in the embodiment shown in the figure, and in other embodiments different from the embodiment shown in the figure, the number of the middle frame units 3b may be other, such as one or more. In the assembled state as shown in fig. 2, the middle frame unit 3b is positioned between the two side frame units 3 a. Wherein each frame element 3a has reinforcing connecting ribs 30a which are located on both sides of the thrust reverser cascade in the assembled state as shown in fig. 2, the reinforcing connecting ribs 30a having a greater thickness than the connecting ribs 30, wherein the rib thickness can be defined on the basis of the strength analysis results.

Further, the intermediate frame unit 3b is plural as shown in the figure, and each of the intermediate frame units 3b has the same configuration.

Further, the blade units 31 in the middle frame unit 3b and the frame unit 3a have the same length as shown in the figure. The arrangement is that the two frame units 3a have the same configuration, the plurality of middle frame units 3b have the same configuration, the grid configurations of the frame units 3a and the middle frame units 3b are completely consistent, a set of core moulds can be shared in the manufacturing process, and all moulds in the forming process can be shared due to the consistent configuration of the middle frame units 3 b.

In one embodiment of the thrust reverser cascade, the intermediate frame units 3 are fixedly connected, such as by bonding or welding in some embodiments, and the intermediate frame units 3 are connected by fasteners in other embodiments, so as to further ensure the structural strength of the assembled thrust reverser cascade.

Fig. 4 is a perspective view of an embodiment of the first member, please refer to fig. 1, fig. 3, and fig. 4 in combination. In one embodiment of the thrust reverser cascade, the first connection 110 is a first groove provided in the first connection surface 11, the second connection 210 is a second groove provided in the second connection surface 21, the third connection 33 is a first lug extending inwardly at one end of the connecting rib 3, and the fourth connection 34 is a second lug extending inwardly at the other end of the connecting rib 3. Wherein, the first lug is fixedly connected with the bottom wall of the first slot part, and the second lug is fixedly connected with the bottom wall of the second slot part, so that the assembly among the first member 1, the second member 2 and the blade grid unit body 3 is completed. The clamping groove sunken design is adopted, so that the connected structure has a smooth profile, and the performance requirement of the reverse thrust blade cascade is ensured. In some embodiments, the intermediate frame unit 3 is bonded or welded to the first member 1 and/or the second member 2, and in other embodiments, the intermediate frame unit 3 is bonded to the first member 1 and/or the second member 2 using fasteners. In other embodiments different from those shown, the first connecting portion 110, the second connecting portion 210 may be tenons, and the third connecting portion 33 and the fourth connecting portion 34 may be mortises matched with the tenons.

With continued reference to fig. 1 and 4, the first member 1 has a first rim 12 and a first connecting plate 13, the first rim 12 provides the front connecting edge 10, and the first connecting portion 13 provides the first connecting surface 11. The second component 2 has a second rim 22 and a second connection plate 23, the second rim 22 providing the rear connection edge 20 and the second connection plate 23 providing the second connection face 21.

The thrust reverser cascade as in one or more of the preceding embodiments may be made of composite material to achieve weight reduction requirements.

The thrust reverser cascade as in one or more of the preceding embodiments can be used in a thrust reverser comprising a thrust reverser cascade, a torque box and a cascade support ring, the front connecting edge 10 of the thrust reverser cascade being connected to the torque box and the rear connecting edge 20 being connected to the cascade support ring.

The thrust reverser as described above may be used in an aircraft engine, the thrust reverser being arranged in an engine nacelle of the aircraft engine.

Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention, and those skilled in the art can make various changes and modifications without departing from the spirit and scope of the present invention. Therefore, any modification, equivalent changes and modifications made to the above embodiments according to the technical spirit of the present invention, all without departing from the content of the technical solution of the present invention, fall within the scope of protection defined by the claims of the present invention.

Claims

1. A thrust reverser cascade comprising:

2. The thrust reverser cascade of claim 1 wherein each cascade unit body comprises a pair of tie bars and a plurality of blade units connected between the pair of tie bars.

3. The thrust reverser cascade of claim 2, wherein the plurality of cascade unit bodies include two side frame units and at least one middle frame unit, the middle frame unit being positioned between the two side frame units in the assembled state;

4. The thrust reverser cascade of claim 3 wherein the intermediate frame element is a plurality of intermediate frame elements, the plurality of intermediate frame elements having the same configuration.

5. The thrust reverser cascade of claim 3 wherein the vane elements in the center frame element and the edge frame element are the same length.

6. The thrust reverser cascade of claim 3 wherein the intermediate frame elements are fixedly connected to one another.

7. The thrust reverser cascade of claim 1 wherein the first connection section is a first slot section disposed in the first connection face, the second connection section is a second slot section disposed in the second connection face, the third connection section is a first lug extending inboard at one end of the connection rib, and the fourth connection section is a second lug extending inboard at the other end of the connection rib;

8. The thrust reverser cascade of claim 7 wherein,

the first member has a first rim providing the front connecting edge and a first connecting plate providing the first connecting face;

9. A thrust reverser comprising a thrust reverser cascade, a torque box and a cascade support ring, wherein the thrust reverser cascade is a thrust reverser cascade according to any one of claims 1 to 8;

10. An aircraft engine comprising a nacelle, wherein a thrust reverser as claimed in claim 9 is provided in the nacelle.