Distributed feeding device of aero-engine

Abstract

The invention relates to an aero-engine distributed feeding device which comprises a feeding header pipe and a plurality of distributing pipes, the distributing pipes are communicated with the feeding header pipe, the length direction of the feeding header pipe surrounds the periphery of a casing of an aero-engine to form a closed loop shape, convex ribs are arranged on the surface of the casing, and supporting structures are further arranged between the convex ribs and the distributing pipes. The supporting structure comprises a hoop and a support, the hoop comprises a hoop ring and a damping plate, the hoop ring is in the shape of a multi-layer closed circular ring surrounding the periphery of the material distribution pipe, the damping plate is in the shape of a multi-layer thin plate, the hoop ring and the damping plate are integrally manufactured and formed by adopting and only one steel belt through repeated roundabout folding, and the support is fixedly connected between the damping plate and the convex rib. By adopting the technical scheme provided by the invention, the supporting structure can absorb the vibration of the material distributing pipe and also reduce the assembly error between the material distributing pipe and other parts, so that the relative positions of the parts are kept stable, the assembly accumulative error is reduced, and the operation efficiency of an engine is improved.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of aero-engines, and particularly relates to a distributed fuel supply device of an aero-engine. BACKGROUND

[0002] An aero-engine is a highly complex and precise heat engine, as the heart of an airplane, not only the power of the airplane flight, but also an important driving force for promoting the development of the aviation industry. When the aero-engine is running, fuel, oil or gas needs to be continuously supplied into the combustion chamber. In order to make the combustion more sufficient, fuel, oil or gas needs to be supplied to multiple positions in the combustion chamber at the same time, which is usually called a distributed fuel supply mode. The distributed fuel supply mode is widely used in various heat engines.

[0003] For example, the patent document with the publication number: CN210979849U discloses an automatic continuous operation corpse cremator system, which comprises a cremator and a corpse bed transmission system. The cremator comprises a furnace body, a plurality of independent igniters and a plurality of fuel atomizers distributed in the furnace body, a fuel supply controller connected with the fuel atomizers, and a fuel supply system arranged outside the furnace body. The corpse bed transmission system mainly comprises an in-furnace transmission mechanism located in the furnace body, a corpse bed replacement mechanism connected with the in-furnace transmission mechanism, and a front vehicle transmission mechanism connected with the corpse bed replacement mechanism. The corpse bed is transmitted from the front vehicle transmission mechanism to the corpse bed replacement mechanism, and then to the in-furnace transmission mechanism for cremation operation. The patent technology adopts a multi-point circulating atomizing fuel supply system, so that the corpse can be burned as quickly and completely as possible, and the cremation efficiency is improved.

[0004] However, the existing distributed fuel supply device generally comprises a feeding main pipe and a plurality of branch pipes. One end of the branch pipe is rigidly connected with and communicated with the feeding main pipe, and the other end of the branch pipe is aligned with a fixed position in the engine case. The branch pipe and the feeding main pipe are rigidly connected together, which is not convenient for adjusting the direction of the branch pipe and the relative position between the branch pipe and the feeding main pipe. In addition, since each component has a machining error, the feeding main pipe and the branch pipe are not an exception. The assembled distributed fuel supply device has a large assembly error, which leads to a large difference between the actual fuel supply position and the theoretically designed position, affecting the running efficiency of the aero-engine. In addition, when the aero-engine is running, the vibration generated in the external environment will be transmitted to the feeding main pipe and the branch pipe, causing the structure of the distributed fuel supply device to loosen, the relative position between some components changes, which also increases the assembly error, leading to a large difference between the actual fuel supply position and the theoretically designed position, affecting the running efficiency of the aero-engine. SUMMARY

[0005] To solve the above technical problems, the present application provides an aero-engine distributed feeding device.

[0006] The present application provides an aero-engine distributed feeding device, comprising a feeding main pipe and a plurality of branch pipes, the branch pipes are communicated with the feeding main pipe, and the length direction of the feeding main pipe is in a closed loop shape along the circumference of the aero-engine casing, the surface of the casing is provided with a convex rib, and a supporting structure is further provided between the convex rib and the branch pipe, the supporting structure comprises a clamp and a bracket, the clamp comprises a hoop and a damping plate, the hoop is a multi-layer closed circular shape around the branch pipe, and the damping plate is a multi-layer thin plate shape, the hoop and the damping plate are integrally formed by using one steel strip to fold back and forth for multiple times, and the bracket is fixed between the damping plate and the convex rib.

[0007] The aero-engine distributed feeding device further comprises a first screw rod and a second screw rod, the bracket comprises a horizontal connecting plate, a pressure relief plate and a vertical supporting plate, the pressure relief plate is fixed between the horizontal connecting plate and the vertical supporting plate, one end of the first screw rod is provided with a first boss, the other end of the first screw rod is screwed with the horizontal connecting plate, and the damping plate is clamped between the first boss and the horizontal connecting plate, the surface of the second screw rod is provided with a second boss, one end of the second screw rod is screwed with a first nut, the other end of the second screw rod is screwed with a second nut, and the convex rib is clamped between the second boss and the first nut, and the vertical supporting plate is clamped between the second boss and the second nut.

[0008] The horizontal connecting plate, the pressure relief plate and the vertical supporting plate are integrally formed.

[0009] The pressure relief plate is a circular arc thin plate.

[0010] At least a part of the first nut is nested in the convex rib.

[0011] Resilient washers are further clamped between the second nut and the vertical supporting plate, and between the damping plate and the first boss.

[0012] The aero-engine distributed feeding device further comprises a guide head, a spraying pipe and a nut, the guide head is provided with a dosing chamber, the branch pipe and the feeding main pipe are communicated with the dosing chamber, the spraying pipe is provided with a feeding hole and a shooting hole, one end of the shooting hole is aligned with the casing, the other end of the shooting hole is communicated with the feeding hole, the spraying pipe is screwed with the nut, the spraying pipe penetrates the dosing chamber, and the feeding hole is accommodated in the dosing chamber.

[0013] Sealing rings are further provided between the nut and the guide head, and between the spraying pipe and the guide head.

[0014] The filter is embedded in the injection hole, and the surface of the filter is provided with a flow guide groove, a flow distribution groove, a flow gathering groove and a plurality of fins.

[0015] The surface of the filter is further provided with a backflow groove and an overflow hole, one end of the backflow groove is communicated with the flow guide groove, the other end of the backflow groove is open and close to the screw cap, the overflow hole is arranged between the screw cap and the flow guide groove, and the overflow hole is communicated with the injection hole, and the fins are further arranged between the backflow groove and the overflow hole.

[0016] The beneficial effects of the present application are that: by adopting the technical scheme provided by the present application, the support structure is arranged between the convex rib of the casing and the distribution pipe, the support structure comprises a clamp and a support, the clamp comprises a hoop and a damping plate, and the hoop and the damping plate are both multi-layer thin plate structures, on the one hand, the vibration from the distribution pipe can be absorbed, the structure of the distributed fuel supply device is prevented from loosening, the relative positions between the parts are kept stable, the assembly error is prevented from increasing, and the operation efficiency of the aero-engine is improved; on the other hand, the support structure can slide along the length direction of the distribution pipe, the distribution pipe can rotate along the inner circumferential surface of the hoop, and the relative position or the relative angle between the support and the convex rib of the surface of the casing can also be adjusted, so that the relative position between the distribution pipe and the feed main pipe is facilitated to be adjusted, the assembly cumulative error is reduced, the actual fuel supply position is kept consistent with the theoretical design position as much as possible, and the operation efficiency of the aero-engine is further improved. BRIEF DESCRIPTION OF DRAWINGS

[0017] Figure 1 is the axonometric view of the present application; Figure 2 is the axonometric view of the support structure of the present application; Figure 3 is the front view along the present support structure; Figure 4 is the front view of the clamp of the present application; Figure 5 is the front view of the filter structure of the present application; Figure 6 is the exploded view of the filter structure of the present application; Figure 7 is the front view of the guide head of the present application; Figure 8 is the front view of the injection pipe of the present application; Figure 9 is the axonometric view of the filter of the present application.

[0018] In the figure: 1 - total feeding pipe, 2 - branch pipe, 3 - casing, 4 - convex rib, 5 - supporting structure, 6 - clamp, 7 - support, 8 - hoop, 9 - shock absorbing plate, 10 - first screw, 11 - second screw, 12 - flat plate, 13 - pressure relief plate, 14 - vertical support plate, 15 - first boss, 16 - second boss, 17 - first nut, 18 - second nut, 19 - elastic washer, 20 - limiting hole, 21 - bushing, 22 - guide head, 23 - feeding pipe, 24 - nut, 25 - mixing chamber, 26 - feeding hole, 27 - injection hole, 28 - sealing ring, 29 - accommodating groove, 30 - filter, 31 - flow guide groove, 32 - branch groove, 33 - converging groove, 34 - fin, 35 - return groove, 36 - overflow hole, 37 - stop ring, 38 - positioning step. DETAILED DESCRIPTION

[0019] The technical solutions of the present application are further described below in combination with the drawings, but the scope of protection required is not limited to the description; The present application provides a kind of distributed fuel supply device of aero-engine, as shown in Figures 1 to 9 Fig. 1, including total feeding pipe 1 and several branch pipes 2, branch pipe 2 is communicated with total feeding pipe 1, and the length direction of total feeding pipe 1 is along the casing 3 of aero-engine around closed loop shape, the surface of casing 3 is provided with convex rib 4, and supporting structure 5 is further provided between convex rib 4 and branch pipe 2, supporting structure 5 includes clamp 6 and support 7, clamp 6 includes hoop 8 and shock absorbing plate 9, hoop 8 is the closed circular shape of multiple layers around branch pipe 2, shock absorbing plate 9 is the shape of multiple layers of thin plate, hoop 8 and shock absorbing plate 9 are shaped by using and only one steel belt is folded back and integrated, and support 7 is fixed between shock absorbing plate 9 and convex rib 4.

[0020] By using the technical solutions provided by the present application, the convex rib of the casing and the branch pipe are provided with supporting structure, the supporting structure includes clamp and support, the clamp includes hoop and shock absorbing plate, the hoop and the shock absorbing plate are both multiple layers of thin plate structure, on the one hand, the vibration from the branch pipe can be absorbed, the structure of the distributed fuel supply device is prevented from loosening, the relative position between parts is kept stable, the assembly error is prevented from increasing, and the operation efficiency of the aero-engine is improved; on the other hand, the supporting structure can slide along the length direction of the branch pipe, the branch pipe can rotate along the inner circumferential surface of the hoop, and the relative position or the relative angle of the support and the convex rib of the surface of the casing can also be adjusted, so that the relative position between the branch pipe and the total feeding pipe is easily adjusted, the assembly cumulative error is reduced, the actual fuel supply position is kept consistent with the theoretical design position as much as possible, and the operation efficiency of the aero-engine is further improved.

[0021] Specifically, the aero-engine distributed feeding device further comprises a first screw rod 10 and a second screw rod 11, the support 7 comprises a horizontal connecting plate 12, a pressure relief plate 13 and a vertical supporting plate 14, the pressure relief plate 13 is fixedly connected between the horizontal connecting plate 12 and the vertical supporting plate 14, one end of the first screw rod 10 is provided with a first boss 15, the other end of the first screw rod 10 is screwed with the horizontal connecting plate 12, and the damping plate 9 is clamped between the first boss 15 and the horizontal connecting plate 12, the surface of the second screw rod 11 is provided with a second boss 16, one end of the second screw rod 11 is screwed with a first nut 17, the other end of the second screw rod 11 is screwed with a second nut 18, and the lug 4 is clamped between the second boss 16 and the first nut 17, and the vertical supporting plate 14 is clamped between the second boss 16 and the second nut 18. By adopting the technical scheme of the present application, since the pressure relief plate 13 is arranged between the horizontal connecting plate 12 and the vertical supporting plate 14, the pressure relief plate 13 is a circular arc thin plate, on the one hand, the pressure relief plate 13 can be used to release the residual stress accumulated in the manufacturing process of the support 7, which helps to keep the structure of the distributed feeding device stable and prolong the service life of the parts; on the other hand, the pressure relief plate 13 is a circular arc thin plate, and also has a slight adjustment flexibility, so that the orientation of the distribution pipe 2 relative to the casing can be easily adjusted, and the operator can also reduce the corresponding assembly error when assembling the distributed feeding device.

[0022] In addition, the edge of the vertical supporting plate 14 is provided with a limiting opening 20, the limiting opening 20 is a waist-round notch, and the second screw rod 11 penetrates through the limiting opening 20. The distribution pipe 2 also penetrates through at least two bushings 21, and the bushings 21 are tightly attached to the left and right sides of the hoop 8. The horizontal connecting plate 12, the pressure relief plate 13 and the vertical supporting plate 14 are integrally formed. The pressure relief plate 13 is a circular arc thin plate.

[0023] In addition, at least a part of the first nut 17 is nested in the lug 4. The second nut 18 and the vertical supporting plate 14, and the damping plate 9 and the first boss 15 are respectively clamped with elastic washers 19.

[0024] Specifically, the distributed fuel supply device of the aero-engine further comprises a guide head 22, a fuel injection pipe 23 and a nut 24, the guide head 22 is internally provided with a dosing chamber 25, the distribution pipe 2 and the fuel inlet main pipe 1 are communicated with the dosing chamber 25, the fuel injection pipe 23 is internally provided with a fuel injection hole 26 and a fuel injection hole 27, one end of the fuel injection hole 27 is aligned in the engine case 3, the other end of the fuel injection hole 27 is communicated with the fuel injection hole 26, the fuel injection pipe 23 is screwed with the nut 24 and penetrates the dosing chamber 25, and the fuel injection hole 26 is accommodated in the dosing chamber 25. The guide head 22, the fuel injection pipe 23, the nut 24 and the like constitute a filtering structure, fuel first enters the dosing chamber 25 through the guide head, then is distributed into the fuel injection hole 26 and the filter 30 through the dosing chamber 25, the filter 30 is used for filtering impurities in the fuel, and finally the purified fuel is sent into the engine case through the fuel injection hole 27, and since the impurities in the fuel are filtered, the fuel can be more fully combusted, more heat energy is released, and the operation efficiency of the aero-engine is improved.

[0025] In addition, the axial direction of the fuel injection pipe 23 is consistent with the axial direction of the fuel injection hole 27, and the axial direction of the fuel injection hole 26 is perpendicular to the axial direction of the fuel injection hole 27. The sealing ring 28 is arranged between the nut 24 and the guide head 22 and between the fuel injection pipe 23 and the guide head 22. The surface of the guide head 22 is provided with a receiving groove 29, and the sealing ring 28 is accommodated in the receiving groove 29.

[0026] In addition, the filter 30 is embedded in the fuel injection hole 27, the surface of the filter 30 is provided with a flow guide groove 31, a flow distribution groove 32, a flow gathering groove 33 and a plurality of fins 34, the flow guide groove 31 is a circular ring shape, the fuel injection hole 26 is communicated with the flow guide groove 31, one end of the flow distribution groove 32 is communicated with the flow guide groove 31, the other end of the flow distribution groove 32 is away from the nut 24 and is closed, one end of the flow gathering groove 33 is closed, the other end of the flow gathering groove 33 is away from the nut 24 and is communicated with the fuel injection hole 27, and the fins 34 are arranged between the flow distribution groove 32 and the flow gathering groove 33. The number of the flow distribution groove 32 and the flow gathering groove 33 is multiple, and the flow distribution groove 32 and the flow gathering groove 33 are arranged staggered along the circumferential direction of the filter 30. According to the technical scheme of the present application, fuel first enters the flow guide groove 31 of the filter 30, is distributed through the flow distribution groove 32, and then flows through the fins 34 due to the closed end of the flow distribution groove 32, the fins 34 are used for adsorbing impurities in the fuel, so that the fuel is purified, and finally enters the fuel injection hole 27 through the flow gathering groove 33. The fins 34 are in the shape of a circular ring sheet around the outer circumferential surface of the filter 30.

[0027] Specifically, the surface of the filter 30 is further provided with a backflow groove 35 and an overflow hole 36, one end of the backflow groove 35 is communicated with the flow guide groove 31, the other end of the backflow groove 35 is opened and close to the screw cap 24, the overflow hole 36 is arranged between the screw cap 24 and the flow guide groove 31, the overflow hole 36 is communicated with the material injection hole 27, and the fin 34 is further arranged between the backflow groove 35 and the overflow hole 36. According to the technical scheme of the present application, the fuel first enters the flow guide groove 31 of the filter 30, a part of the fuel also enters the backflow groove 35, the end of the backflow groove 35 is close to the screw cap 24, due to the blocking effect of the screw cap 24, the fuel has to flow through the fin 34, the fin 34 is used for adsorbing impurities in the fuel, so that the fuel is purified, and finally enters the material injection hole 27 through the overflow hole 36, so that the impurities in the fuel are fully filtered out to the maximum extent.

[0028] Further, the number of the backflow groove 35 and the overflow hole 36 is multiple, and the backflow groove 35 and the overflow hole 36 are staggered along the circumference of the filter 30. The material injection hole 27 is further embedded with a check ring 37, the material injection hole 27 is further provided with a positioning step 38, and the filter 30 is arranged between the check ring 37 and the positioning step 38. According to the technical scheme of the present application, the filter 30 is convenient to assemble and disassemble, and the filter 30 is convenient to disassemble for regular cleaning.

Claims

1. A distributed feed device for an aeroengine, characterized in that: The application relates to an aero-engine distributed feeding device, which comprises a feeding main pipe (1) and a plurality of feeding branch pipes (2), the feeding branch pipes (2) are communicated with the feeding main pipe (1), the length direction of the feeding main pipe (1) is in a closed loop shape along the periphery of an aero-engine casing (3), the surface of the casing (3) is provided with a convex rib (4), a supporting structure (5) is further arranged between the convex rib (4) and the feeding branch pipe (2), the supporting structure (5) comprises a clamp hoop (6) and a support (7), the clamp hoop (6) comprises a hoop ring (8) and a damping plate (9), the hoop ring (8) is a multi-layer closed circular ring shape surrounding the feeding branch pipe (2), the damping plate (9) is a multi-layer thin plate shape, the hoop ring (8) and the damping plate (9) are integrally formed by adopting one steel strip to be folded back and forth for multiple times, and the support (7) is fixedly connected between the damping plate (9) and the convex rib (4).

2. A distributed supply device for a gas turbine engine as recited in claim 1, wherein: The aero-engine distributed feeding device further comprises a first screw rod (10) and a second screw rod (11), the support (7) comprises a horizontal connecting plate (12), a pressure releasing plate (13) and a vertical supporting plate (14), the pressure releasing plate (13) is fixedly connected between the horizontal connecting plate (12) and the vertical supporting plate (14), one end of the first screw rod (10) is provided with a first boss (15), the other end of the first screw rod (10) is screwed with the horizontal connecting plate (12), and the damping plate (9) is clamped between the first boss (15) and the horizontal connecting plate (12), the surface of the second screw rod (11) is provided with a second boss (16), one end of the second screw rod (11) is screwed with a first nut (17), the other end of the second screw rod (11) is screwed with a second nut (18), and the convex rib (4) is clamped between the second boss (16) and the first nut (17), and the vertical supporting plate (14) is clamped between the second boss (16) and the second nut (18).

3. A distributed feed device for a gas turbine engine as recited in claim 2, wherein: The horizontal connecting plate (12), the pressure releasing plate (13) and the vertical supporting plate (14) are integrally formed.

4. A distributed feed device for a gas turbine engine as set forth in either of claims 2 or 3, characterized in that: The pressure releasing plate (13) is a circular arc thin plate.

5. A distributed supply device for a gas turbine engine as recited in claim 2, wherein: At least a part of the first nut (17) is embedded in the convex rib (4).

6. A distributed feed device for a gas turbine engine as recited in claim 2, wherein: Resilient washers (19) are respectively clamped between the second nut (18) and the vertical supporting plate (14) and between the damping plate (9) and the first boss (15).

7. A distributed supply device for a gas turbine engine as recited in claim 1, wherein: The aero-engine distributed feeding device further comprises a guide head (22), a feeding pipe (23) and a screw cap (24), the guide head (22) is internally provided with a dosing chamber (25), the feeding branch pipe (2) and the feeding main pipe (1) are communicated with the dosing chamber (25), the feeding pipe (23) is internally provided with a feeding hole (26) and a jetting hole (27), one end of the jetting hole (27) is aligned with the casing (3), the other end of the jetting hole (27) is communicated with the feeding hole (26), the feeding pipe (23) is screwed with the screw cap (24), the feeding pipe (23) penetrates through the dosing chamber (25), and the feeding hole (26) is accommodated in the dosing chamber (25).

8. A distributed feed device for a gas turbine engine as recited in claim 7, wherein: Sealing rings (28) are arranged between the screw cap (24) and the guide head (22) and between the feeding pipe (23) and the guide head (22).

9. A distributed feed device for a gas turbine engine as recited in claim 7, wherein: The filter (30) is embedded in the injection hole (27), and the surface of the filter (30) is provided with a flow guide groove (31), a flow distribution groove (32), a flow gathering groove (33) and a plurality of fins (34). The flow guide groove (31) is in the shape of a ring, and the injection hole (26) is in communication with the flow guide groove (31). One end of the flow distribution groove (32) is in communication with the flow guide groove (31), and the other end of the flow distribution groove (32) is away from the screw cap (24) and is closed. One end of the flow gathering groove (33) is closed, and the other end of the flow gathering groove (33) is away from the screw cap (24) and is in communication with the injection hole (27). The fins (34) are arranged between the flow distribution groove (32) and the flow gathering groove (33).

10. A distributed feed device for a gas turbine engine as recited in claim 9, wherein: The surface of the filter (30) is further provided with a backflow groove (35) and an overflow hole (36). One end of the backflow groove (35) is in communication with the flow guide groove (31), and the other end of the backflow groove (35) is open and close to the screw cap (24). The overflow hole (36) is arranged between the screw cap (24) and the flow guide groove (31), and the overflow hole (36) is in communication with the injection hole (27). The fins (34) are further arranged between the backflow groove (35) and the overflow hole (36).

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