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CN-121988649-A - Fuel conduit bending equipment of aero-engine

CN121988649ACN 121988649 ACN121988649 ACN 121988649ACN-121988649-A

Abstract

The invention relates to the technical field of bending equipment and discloses aeroengine fuel guide pipe bending equipment which comprises a main body mechanism, an auxiliary mechanism and a clamping assembly, wherein the main body mechanism comprises a workbench and a bending assembly arranged at one end of the workbench, and the auxiliary mechanism comprises a moving assembly arranged at the top of the workbench and the clamping assembly arranged at the top of the moving assembly. According to the invention, through the synergistic effect of the moving assembly, the clamping assembly, the rotating assembly and the bending assembly, the automatic feeding, the accurate clamping, the multi-angle positioning and the accurate bending of the fuel oil guide pipe of the aeroengine are realized, the production and processing precision of the guide pipe is greatly improved, the guide assembly effectively prevents the shaking, the instability and the pipe wall wrinkling of the guide pipe in the bending process through the adjustable supporting wheel structure, the bending forming quality is ensured, the power assembly and the moving assembly are cooperatively driven, the auxiliary power is provided for the feeding of the guide pipe, and the processing precision of the long guide pipe and the multi-elbow is remarkably improved.

Inventors

  • WANG HONGMING
  • WANG ZHIHAO

Assignees

  • 上海民航职业技术学院

Dates

Publication Date
20260508
Application Date
20260316

Claims (10)

  1. 1. The fuel pipe bending equipment of the aeroengine is characterized by comprising, A main body mechanism (100) comprising a workbench (101), a bending assembly (102) arranged at one end of the workbench (101), and The auxiliary mechanism (200) comprises a moving assembly (201) arranged at the top of the workbench (101), a clamping assembly (202) arranged at the top of the moving assembly (201), a rotating assembly (203) arranged outside the clamping assembly (202), a guide assembly (204) arranged at one end of the top of the workbench (101) and a power assembly (205) arranged on the guide assembly (204).
  2. 2. The aeroengine fuel conduit bending device according to claim 1, wherein the moving assembly (201) comprises a feeding track (201 a) symmetrically arranged on the top of the workbench (101), a bearing plate (201 b) in sliding fit with the two feeding tracks (201 a), a conveying motor (201 c) arranged on the top of the bearing plate (201 b), a conveying gear (201 d) arranged at the output end of the conveying motor (201 c), and a rack (201 e) arranged on the top of the workbench (101) and meshed with the conveying gear (201 d).
  3. 3. The bending equipment for the fuel pipe of the aeroengine according to claim 2, wherein the clamping assembly (202) comprises a supporting installation seat (202 a) arranged on the top of the bearing plate (201 b), a first servo motor (202 b) arranged on one side of the supporting installation seat (202 a), and a first driving gear (202 c) arranged at the output end of the first servo motor (202 b).
  4. 4. An aeroengine fuel conduit bending apparatus as claimed in claim 3, wherein the clamping assembly (202) further comprises a first driven gear (202 d) arranged on one side of the first driving gear (202 c), a transmission pipeline (202 e) arranged on the inner surface of the first driven gear (202 d), a threaded sleeve (202 f) sleeved on the surface of the transmission pipeline (202 e) and in threaded connection with the transmission pipeline, and a clamping piece (202 g) fixedly arranged at the end part of the threaded sleeve (202 f).
  5. 5. The aeroengine fuel conduit bending equipment according to claim 4, wherein the clamping piece (202 g) comprises a mounting sleeve (202 g-1) fixedly mounted at the end part of the threaded sleeve (202 f), a plurality of movable plates (202 g-2) circumferentially arrayed on the surface of the mounting sleeve (202 g-1), two guide rods (202 g-3) symmetrically penetrating through the movable plates (202 g-2) and fixed with the surface of the mounting sleeve (202 g-1), and a return spring (202 g-4) sleeved outside the guide rods (202 g-3); The movable plate (202 g-2) is provided with a guide bar for sliding the mounting sleeve (202 g-1), and two ends of the reset spring (202 g-4) are fixedly connected with the mounting sleeve (202 g-1) and the movable plate (202 g-2) respectively.
  6. 6. The bending equipment for the fuel pipe of the aeroengine, as set forth in claim 5, wherein the clamping piece (202 g) further comprises a limiting block (202 g-5) arranged on the outer side of the movable plate (202 g-2), and a clamping block (202 g-6) arranged on the inner side of the limiting block (202 g-5).
  7. 7. The aircraft engine fuel duct bending apparatus as set forth in claim 6, wherein said rotating assembly (203) comprises a second servomotor (203 a) disposed on top of said support mount (202 a), a second driving gear (203 b) disposed at an output end of said second servomotor (203 a), a second driven gear (203 c) disposed on one side of said second driving gear (203 b), and a steering drive shaft (203 d) disposed on an inner surface of said second driven gear (203 c); One end of the steering driving shaft (203 d) is provided with a circumferential array of guide grooves, the number of which is the same as that of the limiting blocks (202 g-5) and used for being matched with the limiting blocks, and the guide grooves are attached to the inclined surfaces of the limiting blocks (202 g-5).
  8. 8. The aeroengine fuel conduit bending equipment according to claim 7, wherein the guide assembly (204) comprises a bearing frame (204 a) arranged at one end of the top of the workbench (101), an adjusting motor (204 b) arranged at the top of the bearing frame (204 a), a bidirectional threaded rod (204 c) arranged at the output end of the adjusting motor (204 b), an upper guide block (204 d) arranged at the upper section of the bidirectional threaded rod (204 c), an upper supporting wheel (204 e) arranged at the inner side of the upper guide block (204 d) in a rotating way through a rotating shaft, a lower guide block (204 f) arranged at the lower section of the bidirectional threaded rod (204 c), a lower supporting wheel (204 g) arranged at the inner side of the lower guide block (204 f) in a rotating way through the rotating shaft, and a limiting column (204 h) penetrating through the upper guide block (204 d) and the lower guide block (204 f) and fixed at the inner side of the bearing frame (204 a).
  9. 9. The aircraft engine fuel duct bending apparatus as set forth in claim 8, wherein the power assembly (205) comprises an auxiliary motor (205 a) disposed on one side of the upper guide block (204 d), and a belt transmission member (205 b) having both ends fixedly connected to an output end of the auxiliary motor (205 a) and a rotating shaft of the upper support wheel (204 e), respectively.
  10. 10. The bending device for the fuel pipe of the aeroengine, as set forth in claim 9, wherein the bending assembly (102) comprises a first working cylinder (102 a) arranged at one end of the workbench (101), a fixed supporting block (102 b) arranged at the output end of the first working cylinder (102 a), a mounting frame (102 c) arranged at one end of the workbench (101), a bending motor (102 d) arranged on the mounting frame (102 c), a rotating bending block (102 e) arranged at the output end of the bending motor (102 d), a second working cylinder (102 f) arranged on the mounting frame (102 c), and a rotating supporting block (102 g) arranged at the output end of the second working cylinder (102 f).

Description

Fuel conduit bending equipment of aero-engine Technical Field The invention relates to the technical field of bending equipment, in particular to bending equipment for fuel pipes of an aero-engine. Background The fuel conduit is a key component of the fuel system of the engine and is responsible for accurately delivering fuel to the combustion chamber in a complex working environment, and because the fuel conduit needs to be distributed in a very limited space and avoid a plurality of other components, the conduit is usually designed into a space bent pipe with a complex three-dimensional shape, the complex configuration puts very high requirements on the manufacturing precision of the conduit, and any tiny shape deviation, section deformation or surface damage can cause fuel leakage, pressure loss or uneven flow, thereby affecting the overall performance of the engine and even causing serious potential safety hazards. At present, the manufacture of the fuel conduit of the aeroengine, particularly the bending process, still faces great challenges, when the traditional pipe bending equipment is applied to the high-standard aviation conduit processing, the clamping force is controlled inaccurately, the surface of the conduit is easy to crush or clamp loose to cause slipping, some equipment lacks effective support and guide of the conduit near bending points, the conduit is unstable and distorted due to overlong suspended sections when being bent, the feeding resistance of the conduit is large when the long conduit or the multi-elbow conduit is processed, the feeding slipping or the conduit twisting is easy to occur only by means of single feeding mechanism driving, the dimensional precision of each bending section is inconsistent, and the complex processing requirement of the fuel conduit of the aeroengine is difficult to adapt. Disclosure of Invention The invention is provided in view of the problems of the prior fuel pipe bending equipment of the aeroengine. Therefore, the invention aims to provide bending equipment for the fuel pipe of the aeroengine. In order to solve the technical problems, the invention provides the following technical proposal that comprises, The main body mechanism comprises a workbench, a bending assembly arranged at one end of the workbench, and The auxiliary mechanism comprises a moving assembly arranged at the top of the workbench, a clamping assembly arranged at the top of the moving assembly, a rotating assembly arranged at the outer side of the clamping assembly, a guide assembly arranged at one end of the top of the workbench and a power assembly arranged on the guide assembly. As a preferable scheme of the aeroengine fuel conduit bending equipment, the moving assembly comprises feeding rails symmetrically arranged at the top of the workbench, a bearing plate in sliding fit with the two feeding rails, a conveying motor arranged at the top of the bearing plate, a conveying gear arranged at the output end of the conveying motor, and a rack arranged at the top of the workbench and meshed with the conveying gear. As a preferable scheme of the aeroengine fuel conduit bending equipment, the clamping assembly comprises a supporting installation seat arranged at the top of the bearing plate, a first servo motor arranged on one side of the supporting installation seat, and a first driving gear arranged at the output end of the first servo motor. As a preferable scheme of the aeroengine fuel conduit bending equipment, the clamping assembly further comprises a first driven gear arranged on one side of the first driving gear, a transmission pipeline arranged on the inner surface of the first driven gear, a thread sleeve sleeved on the surface of the transmission pipeline and in threaded connection with the transmission pipeline, and a clamping piece fixedly arranged at the end part of the thread sleeve. As a preferable scheme of the aeroengine fuel conduit bending equipment, the clamping piece comprises a mounting sleeve fixedly mounted at the end part of the threaded sleeve, a plurality of movable plates circumferentially arranged on the surface of the mounting sleeve, two guide rods symmetrically penetrating through the movable plates and fixed with the surface of the mounting sleeve, and a return spring sleeved outside the guide rods; The movable plate is provided with a guide bar for sliding the mounting sleeve, and two ends of the reset spring are respectively and fixedly connected with the mounting sleeve and the movable plate. As an optimal scheme of the aeroengine fuel conduit bending equipment, the clamping piece further comprises a limiting block arranged on the outer side of the movable plate and a clamping block arranged on the inner side of the limiting block. As a preferable scheme of the aeroengine fuel conduit bending equipment, the rotating assembly comprises a second servo motor arranged at the top of the supporting installation seat, a second driving gear arranged at th