CN111894889B

CN111894889B - Fusing system and aircraft engine

Info

Publication number: CN111894889B
Application number: CN201910370964.8A
Authority: CN
Inventors: 柴象海
Original assignee: AECC Commercial Aircraft Engine Co Ltd
Current assignee: AECC Commercial Aircraft Engine Co Ltd
Priority date: 2019-05-06
Filing date: 2019-05-06
Publication date: 2021-07-06
Anticipated expiration: 2039-05-06
Also published as: CN111894889A

Abstract

The invention aims to provide a fusing system and an aircraft engine. The fusing system comprises a first supporting conical wall for supporting the first bearing, wherein the first supporting conical wall comprises an upper conical wall and a lower conical wall; the upper conical wall is provided with a first combining end, the lower conical wall is provided with a second combining end, and the first combining end and the second combining end are connected in a fusible mode; one of the first combining end and the second combining end is provided with a connector, and the other one is provided with a limiting cavity and a through hole communicated with the limiting cavity; the connector comprises a connecting part, a stop block part and a weak part, wherein the stop block part is respectively connected with the connecting part and the weak part; the block part and the weak part are arranged in the limiting cavity and movably matched with the limiting cavity, wherein the weak part is fixedly connected with the inner wall of the limiting cavity; the connecting part is arranged in the through hole in a penetrating way; the size of the through hole is smaller than that of the stop block part so as to prevent the stop block part from being separated from the limiting cavity. An aircraft engine includes the above-described fusing system.

Description

Fusing system and aircraft engine

Technical Field

The invention relates to the field of aircraft engines, in particular to a fusing system and an aircraft engine.

Background

Aircraft engines may be struck by a bird or the like, causing one or more fan blades to break or fall, i.e., fbo (fan Blade off). After an FBO event occurs, the center of gravity of the fan may be offset from the centerline of the low pressure spool. However, due to the limitations of the bearings, the fan still rotates about the centerline of the low pressure rotor. Rotation of the fan about an axis offset from its center of gravity excites the low pressure rotor system to produce one or more modes of oscillation, thereby producing unbalanced loads. For the large bypass ratio turbofan engine commonly used on the current commercial aircraft, the radius of a fan blade is long, the mass is large, and the FBO event can cause the gravity center line of the fan to be not aligned with the center line of the engine, so that huge unbalanced load is caused. Since the bearings radially constrain the fan rotor, FBO imbalance loads are primarily transferred through the bearings and their support structure to the intermediate case and further to the mounting joints and even the aircraft.

Patent document CN107237655A discloses a fusing structure and method under the flying-off load of a fan blade of an aero-engine, wherein the aero-engine includes a fan rotor, a stator component intermediary casing, a first bearing and a second bearing for supporting the fan rotor, a first supporting conical wall for supporting the first bearing on the stator component intermediary casing, and a second supporting wall for supporting the second bearing on the stator component intermediary casing, the first supporting conical wall is a thin-wall annular structure and includes an upper conical wall and a lower conical wall, the upper conical wall has an upper bonding surface, the lower conical wall has a lower bonding surface, one of the upper bonding surface and the lower bonding surface is a concave spherical surface, the other is a convex spherical surface, the upper bonding surface and the lower bonding surface are complementary to each other and are welded into a fusing structure with the strength smaller than that of a parent material, and the spherical center of the fusing structure is located at the axis of the fan rotor.

In the technical scheme of the above patent document, the concave spherical surface and the convex spherical surface still keep a fitting state after fusing occurs, resulting in an unsatisfactory buffering effect.

Disclosure of Invention

The invention aims to provide a fusing system which has the advantage of good buffering effect.

The invention also aims to provide an aircraft engine which comprises the fusing system.

To achieve the object, a fuse system includes a first supporting conical wall for supporting a first bearing, the first supporting conical wall including an upper conical wall and a lower conical wall; the upper conical wall has a first bonding end, the lower conical wall has a second bonding end, and the first bonding end and the second bonding end are connected in a fusible mode;

one of the first combining end and the second combining end is provided with a connector, and the other one is provided with a limiting cavity and a through hole communicated with the limiting cavity;

the connector comprises a connecting part, a stop block part and a weak part, wherein the stop block part is respectively connected with the connecting part and the weak part;

the block part and the weak part are arranged in the limiting cavity, the block part is movably matched with the limiting cavity, and the weak part is fixedly connected with the inner wall of the limiting cavity; the connecting part is arranged in the through hole in a penetrating mode; the size of the through hole is smaller than that of the stop block part so as to prevent the stop block part from falling out of the limiting cavity.

In one embodiment, the outer peripheral wall of the stop block part is opposite to the inner wall of the limit cavity, and a gap exists.

In one embodiment, the connecting portion is clearance fit with the through hole.

In one embodiment, the inner wall of the limiting cavity comprises a top wall, a side wall and a bottom wall, the top wall is opposite to the bottom wall, the through hole is formed in the top wall, and the weak portion is fixedly connected with the bottom wall.

In one embodiment, the limiting cavity is an annular cavity centered on the axis of the first supporting conical wall; the through hole is an annular through hole which takes the axis of the first supporting conical wall as the center.

In one embodiment, the first supporting cone wall is a thin-walled annular structure.

In one embodiment, the connector further comprises a limiting part, and the limiting part is arranged outside the limiting cavity and connected with the connecting part; the size of the limiting part is larger than that of the through hole.

In one embodiment, the limiting portion, the connecting portion, the stopper portion and the weak portion are annular structures centered on an axis of the first supporting conical wall.

In one embodiment, the first and second bonding ends are manufactured by an additive manufacturing process.

The fusion system aircraft engine for achieving the purpose comprises the fusion system (800) as described above.

The positive progress effects of the invention are as follows: the invention provides a fusing system which comprises a first supporting conical wall used for supporting a first bearing, wherein the first supporting conical wall comprises an upper conical wall and a lower conical wall; the upper conical wall is provided with a first combining end, the lower conical wall is provided with a second combining end, and the first combining end and the second combining end are connected in a fusible mode; one of the first combining end and the second combining end is provided with a connector, and the other one is provided with a limiting cavity and a through hole communicated with the limiting cavity; the connector comprises a connecting part, a stop block part and a weak part, wherein the stop block part is respectively connected with the connecting part and the weak part; the block part and the weak part are arranged in the limiting cavity and movably matched with the limiting cavity, wherein the weak part is fixedly connected with the inner wall of the limiting cavity; the connecting part is arranged in the through hole in a penetrating way; the size of the through hole is smaller than that of the stop block part so as to prevent the stop block part from being separated from the limiting cavity.

Because dog portion and spacing chamber movably cooperate, and the through-hole can block dog portion and deviate from spacing intracavity, consequently, after the fracture takes place for weak part under fusing is adjusted, dog portion is spacing in spacing intracavity by movably to make upper cone wall and lower cone wall can not break away from completely, and the upper cone wall has more degree of freedom for lower cone wall, thereby has better buffering effect.

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 is a schematic illustration of an aircraft engine;

FIG. 2 is a schematic view of a fuse system in which the frangible portion has not yet been broken;

FIG. 3 is an enlarged view at B in FIG. 2;

FIG. 4 is a schematic view of a fuse system in which a weakened portion is broken;

FIG. 5 is an enlarged view at C of FIG. 4;

FIG. 6 is a schematic view of the lower conical wall oscillating in direction D relative to the upper conical wall;

fig. 7 is a schematic view of the lower conical wall oscillating in direction E with respect to the upper conical wall.

Detailed Description

The present invention is further described in the following description with reference to specific embodiments and the accompanying drawings, wherein the details are set forth in order to provide a thorough understanding of the present invention, but it is apparent that the present invention can be embodied in many other forms different from those described herein, and it will be readily appreciated by those skilled in the art that the present invention can be implemented in many different forms without departing from the spirit and scope of the invention.

The following discloses embodiments or examples of various implementations of the subject technology. Specific examples of components and arrangements are described below to simplify the present disclosure, but these are merely examples and do not limit the scope of the invention. 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 fig. 1-7 are exemplary only, are not drawn to scale, and should not be construed as limiting the scope of the invention as actually claimed.

Fig. 1 shows an aircraft engine 900 according to an embodiment of the present invention, which includes a fan rotor 700, a stator-intermediate casing 600, a first bearing 1 (also called a No. 1 bearing) and a second bearing 2 (also called a No. 2 bearing) that support the fan rotor 700, a fusing system 800 that supports the first bearing 1 on the stator-intermediate casing 600, and a second support wall 4 that supports the second bearing 2 on the stator-intermediate casing 600.

As shown in fig. 2, 3, 4 and 5, the fusing system 800 includes a first supporting conical wall 3 for supporting the first bearing 1, the first supporting conical wall 3 including an upper conical wall 31 and a lower conical wall 32; the upper tapered wall 31 has a first coupling end 31a, the lower tapered wall 32 has a second coupling end 32a, and the first coupling end 31a and the second coupling end 32a are fusably coupled.

The fusable link may be a solder, for example, the first bonding end 31a and the second bonding end 32a are integrally soldered by solder, but the strength of the structure formed by solidifying the solder is smaller than the structural strength of the first bonding end 31a and the second bonding end 32a themselves.

However, the welded structure may completely separate the first joining end 31a from the second joining end 32a after the fusion occurs, resulting in complete failure of the aircraft engine 900.

If the technical solution of the patent document CN107237655A is adopted, such that the first connecting end 31a is in spherical fit with the second connecting end 32a, although this solution does not completely separate the first connecting end 31a from the second connecting end 32a, since the first connecting end 31a and the second connecting end 32a are always in surface-to-surface fit, the axial load cannot be buffered, and the buffering effect of the fuse system is poor.

With continued reference to fig. 3 and 5, in one embodiment, one of the first and

second coupling ends

31a and 32a has a connector 310, and the other has a spacing cavity 311 and a through hole 312 communicating with the spacing cavity 311; the connecting head 310 includes a connecting portion 3101, a block portion 3102 and a weak portion 3103, the block portion 3102 being connected to the connecting portion 3101 and the weak portion 3103, respectively; the block portion 3102 and the weak portion 3103 are arranged in the limit cavity 311, wherein the weak portion 3103 is fixedly connected with the inner wall 311a of the limit cavity 311, and the block portion 3102 is movably matched with the limit cavity 311; the connecting portion 3101 is inserted into the through hole 312; the through hole 312 has a size smaller than that of the stopper portion 3102 to block the stopper portion 3102 from coming out of the stopper cavity 311.

In the embodiment shown in fig. 2, 3, 4 and 5, the first coupling end 31a has a limiting cavity 311 and a through hole 312, and the second coupling end 32a has a connector 310.

Because the block portion 3102 is movably matched with the limiting cavity 311, and the through hole 312 can block the block portion 3102 from being released from the limiting cavity 311, when the weak portion 3103 is broken under fusing adjustment, the block portion 3102 is movably limited in the limiting cavity 311, so that the upper conical wall 31 and the lower conical wall 32 cannot be completely separated, and the upper conical wall 31 has more degrees of freedom relative to the lower conical wall 32, thereby having better buffering effect.

As shown in fig. 3 and 5, in a more specific embodiment, the outer peripheral wall of the stopper portion 3102 is disposed opposite to the inner wall 311a of the stopper cavity 311 with a gap. In fig. 3, the stopper portion 3102 has a greater degree of freedom after the occurrence of fuse, because all the outer peripheral walls of the stopper portion 3102 are spaced from the inner wall 311a of the stopper cavity 311. In some embodiments not shown in the drawings, a portion of the outer peripheral wall of the stopper portion 3102 may contact the inner wall 311a of the stopper cavity 311, resulting in a corresponding decrease in the degree of freedom of the stopper portion 3102 after the occurrence of the fusion.

In the embodiment shown in fig. 3 and 5, the connecting portion 3101 is clearance fit with the through hole 312. This arrangement allows the connecting portion 3101 to have a greater degree of freedom after the occurrence of the fusion. In some embodiments not shown in the drawings, the outer peripheral wall of the connecting portion 3101 may come into contact with the inner wall of the through-hole 312, resulting in a corresponding decrease in the degree of freedom of the connecting portion 3101 after the occurrence of the fusion.

With continued reference to fig. 3 and 5, the inner wall 311a of the spacing cavity 311 includes a top wall 311a-1, a side wall 311a-2 and a bottom wall 311a-3, the top wall 311a-1 is disposed opposite to the bottom wall 311a-3, wherein a through hole 312 is opened on the top wall 311a-1, and a weak portion 3103 is fixedly connected to the bottom wall 311 a-3. This arrangement ensures that the stopper portion 3102 has a space for movement in the axial direction of the first supporting conical wall 3 after the weak portion 3103 is broken.

The limiting cavity 311 is an annular cavity which takes the axis A-A of the first supporting conical wall 3 as the center; the through hole 312 is an annular through hole centered on the axis a-a of the first supporting conical wall 3. This arrangement makes the spacing cavity 311 and the through-hole 312 easy to manufacture.

With continued reference to fig. 1, the first supporting cone wall 3 is of thin-walled annular configuration. This solution makes the first supporting cone wall 3 easy to manufacture.

The connector 310 further includes a limiting portion 3104, the limiting portion 3104 is disposed outside the limiting cavity 311 and connected to the connecting portion 3101; the size of the stopper portion 3104 is larger than the size of the through hole 312. The stopper 3104 can abut against the outer wall of the stopper cavity 311 in an extreme situation, and the connection portion 3101 is prevented from being broken by an excessive shearing force.

For ease of manufacture, the stop portion 3104, the connecting portion 3101, the stop portion 3102 and the weakened portion 3103 are annular structures centered on the axis a-a of the first support cone wall 3. The stopper portion 3104, the connecting portion 3101, the stopper portion 3102, and the weak portion 3103 may be integrally molded.

More specifically, the first and second bonding ends 31a and 32a are manufactured by an additive manufacturing process. The mechanism of additive manufacturing is: the method takes metal powder as a raw material, and adopts laser melting/rapid solidification layer-by-layer deposition 'growth manufacturing', and a high-performance structural member is completed by a part CAD model in one step.

As shown in fig. 6 and 7, when the weak portion 3103 is broken, which is the occurrence of fusion, the lower tapered wall 32 swings in the direction D or the direction E with respect to the upper tapered wall 31, and the swung position is shown by the broken line. After fusing occurs, due to the limiting effect of the limiting cavity 311, the lower conical wall 32 can continuously keep the bearing partially constrained on the low-voltage rotating shaft, and the supporting effect is not completely lost.

In addition, according to the load such as shearing force and tensile force generated by the FBO load at the first supporting conical wall 3, the shape and size of the weak portion 3103, the shape and size of the limiting cavity 311 and other parameters can be adjusted to control the relative displacement between the upper conical arm 31 and the lower conical arm 32 after the FBO occurs, so that the low-pressure shaft does not generate radial instantaneous large deformation, the rotor does not generate radial oscillation deformation, the sealing ring of the bearing component is damaged, the lubricating and cooling oil of the component leaks, and the bearing is overheated and jammed in the rotating process.

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 modifications and variations without departing from the spirit and scope of the present invention.

Claims

1. A fuse system comprising a first supporting cone wall (3) for supporting a first bearing (1), said first supporting cone wall (3) comprising an upper cone wall (31) and a lower cone wall (32); the upper conical wall (31) has a first coupling end (31a), the lower conical wall (32) has a second coupling end (32a), and the first coupling end (31a) and the second coupling end (32a) are fusably connected;

one of the first combining end (31a) and the second combining end (32a) is provided with a connecting head (310), and the other one is provided with a limiting cavity (311) and a through hole (312) communicated with the limiting cavity (311);

the connecting head (310) comprises a connecting part (3101), a block part (3102) and a weak part (3103), wherein the block part (3102) is respectively connected with the connecting part (3101) and the weak part (3103);

the block part (3102) and the weak part (3103) are arranged in the limit cavity (311), wherein the weak part (3103) is fixedly connected with the inner wall (311a) of the limit cavity (311), and the block part (3102) is movably matched with the limit cavity (311); the connecting part (3101) is arranged in the through hole (312) in a penetrating way; the size of the through hole (312) is smaller than that of the stop block part (3102) so as to prevent the stop block part (3102) from falling out of the limit cavity (311).

2. The fuse system according to claim 1, wherein an outer peripheral wall of the stopper portion (3102) is disposed opposite to an inner wall (311a) of the stopper cavity (311) with a gap.

3. The fuse system according to claim 1, characterized in that the connecting portion (3101) is clearance fitted with the through hole (312).

4. The fusing system of claim 1, wherein the inner wall (311a) of the limiting chamber (311) comprises a top wall (311a-1), a side wall (311a-2) and a bottom wall (311a-3), the top wall (311a-1) is arranged opposite to the bottom wall (311a-3), wherein the through hole (312) is opened on the top wall (311a-1), and the weak part (3103) is fixedly connected with the bottom wall (311 a-3).

5. A fuse system according to claim 1, characterized in that the limiting chamber (311) is an annular chamber centred on the axis (a-a) of the first supporting conical wall (3); the through hole (312) is an annular through hole which takes the axis (A-A) of the first supporting conical wall (3) as the center.

6. A fuse system according to claim 1, characterized in that the first supporting cone wall (3) is of thin-walled annular configuration.

7. The fusing system of claim 1, wherein the connecting head (310) further comprises a limiting portion (3104), wherein the limiting portion (3104) is disposed outside the limiting cavity (311) and connected to the connecting portion (3101); the size of the limiting part (3104) is larger than that of the through hole (312).

8. The fusing system of claim 7, wherein the position-limiting portion (3104), the connecting portion (3101), the stopper portion (3102) and the weak portion (3103) are annular structures centered on the axis (a-a) of the first supporting conical wall (3).

9. A fuse system according to claim 1, characterized in that the first joining end (31a) and the second joining end (32a) are manufactured by an additive manufacturing process.

10. An aircraft engine, characterized in that it comprises a fusion system (800) according to any one of claims 1 to 9.