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CN-224231271-U - Small turbojet engine vector nozzle test board

CN224231271UCN 224231271 UCN224231271 UCN 224231271UCN-224231271-U

Abstract

The utility model belongs to the technical field of turbojet engine testing, and discloses a vector jet pipe test board of a small turbojet engine, which comprises a fixed platform, a base of a six-component balance is detachably arranged on the fixed platform and used for measuring force and moment generated in the testing process of the turbojet engine, a working platform is fixedly arranged at a measuring end of the six-component balance and used for transmitting the born force and moment to the six-component balance, a fixed mechanism comprises a fixed component which is detachably arranged on the working platform, the turbojet engine to be measured is sleeved in the fixed component by a hoop, and an adjusting component is arranged on the fixed component and is in abutting connection with the outer wall of the turbojet engine. The utility model has compact structure, convenient use, flexible disassembly and assembly, convenient use in outdoor environment, and capability of testing the turbojet engines with different types, realizes multiple purposes, improves the applicability of the test bench, reduces the pressure of storage and transportation, and is convenient for large-scale popularization.

Inventors

  • WANG DONG
  • WANG LIN
  • Huo Xianglong

Assignees

  • 保定市玄云涡喷动力设备研发有限公司

Dates

Publication Date
20260512
Application Date
20250521

Claims (10)

  1. 1. A small turbojet engine vectoring nozzle test stand, comprising: the device comprises a fixed platform (1), wherein the fixed platform (1) is used for fixing the device on a stable platform and bearing thrust; The base of the six-component balance (2) is detachably arranged on the fixed platform (1) and is used for measuring the force and moment generated by the turbojet engine (5) in the test process; The working platform (3) is fixedly arranged at the measuring end of the six-component balance (2) and used for transmitting the born force and moment to the six-component balance (2); The turbojet engine comprises a working platform (3), a fixing mechanism (4), an adjusting component and a turbojet engine (5) to be measured, wherein the fixing mechanism (4) comprises a fixing component which is detachably arranged on the working platform (3), the turbojet engine (5) to be measured is sleeved in the fixing component in a hooped mode, and the adjusting component is arranged on the fixing component and is in butt joint with the outer wall of the turbojet engine (5).
  2. 2. The small turbojet engine vectoring nozzle test stand of claim 1, wherein the bottom end of the fixed platform (1) is detachably connected with a fixing frame (6), and the fixed platform (1) is fixed on the platform through the fixing frame (6).
  3. 3. The small turbojet engine vector nozzle test bench according to claim 1, wherein the fixing assembly comprises a fixing base (7) fixedly installed on the working platform (3), a lifting fixing column (8) is fixedly connected to the top end of the fixing base (7), a fixing ring (9) for sleeving the turbojet engine (5) is fixedly connected to the top end of the fixing column (8), and the adjusting assembly is movably arranged on two sides of the fixing ring (9).
  4. 4. The small turbojet engine vector nozzle test stand of claim 3, wherein the fixed column (8) comprises a fixed pipe (10) fixedly connected to the top end of the fixed base (7), the top end of the fixed pipe (10) is slidably connected with a movable column (11), and the top end of the movable column (11) extends out of the fixed pipe (10) and is fixedly connected with the bottom end of the fixed ring (9).
  5. 5. The small turbojet engine vectoring nozzle test stand according to claim 4, wherein a locking bolt (12) is arranged on the side wall of the fixed pipe (10), and the end part of the locking bolt (12) stretches into the inner cavity of the fixed pipe (10) and is in abutting locking with the outer wall of the movable column (11).
  6. 6. The small turbojet engine vector nozzle test bench according to claim 4, wherein the fixed ring (9) comprises a first semi-ring (13) fixedly connected to the top end of the movable column (11), a second semi-ring (14) is hinged to one side of the first semi-ring (13), the free ends of the second semi-ring (14) are in locking connection through a locking buckle (15), and the turbojet engine (5) is buckled between the first semi-ring (13) and the second semi-ring (14).
  7. 7. The small turbojet engine vector nozzle test bench according to claim 6, wherein a plurality of heat dissipation holes (16) for heat dissipation are formed in the first semi-ring (13) and the second semi-ring (14) in a penetrating manner.
  8. 8. The small turbojet engine vector nozzle test stand according to claim 6, wherein the adjusting assembly comprises a plurality of adjusting screws (17) which are connected with the first semi-ring (13) and the second semi-ring (14) in a threaded mode, the adjusting screws (17) extend into inner cavities of the first semi-ring (13) and the second semi-ring (14) and are rotatably connected with adjusting blocks (18), and the adjusting blocks (18) are abutted to the outer wall of the turbojet engine (5).
  9. 9. The small-sized turbojet engine vectoring nozzle test stand according to claim 8, wherein a flexible contact pad (19) is fixedly connected to one side of the adjusting block (18) away from the adjusting screw (17), and the contact pad (19) is abutted against the outer wall of the turbojet engine (5).
  10. 10. The small turbojet engine vector nozzle test bench according to claim 8, wherein a plurality of abdication grooves (20) which are arranged corresponding to the adjusting blocks (18) are formed in the inner walls of the first semi-ring (13) and the second semi-ring (14), the adjusting screw (17) penetrates through the abdication grooves (20), and the adjusting blocks (18) are telescopically arranged in the abdication grooves (20).

Description

Small turbojet engine vector nozzle test board Technical Field The utility model relates to the technical field of turbojet engine testing, in particular to a vector nozzle test board of a small turbojet engine. Background The performance of a small turbojet engine as an important power source of a modern aircraft is directly related to the flight performance and safety of the aircraft. The vectoring nozzle is used as a key component of the engine, and the maneuverability and stability of the aircraft can be remarkably improved by adjusting the direction and the force of jet air flow. However, conventional small turbojet engine test benches often fail to fully and accurately test the force and moment characteristics of the vectoring nozzle, which limits the improvement and optimization of aeroengine performance. At present, although some testing devices for large-scale aeroengine vector nozzles exist in the market, the devices are huge and high in cost, and are not suitable for the testing requirements of small-scale turbojet engines. In addition, when the small turbojet engine is tested, the equipment may have inaccurate test results or cannot obtain effective conclusions due to the problems of mismatching of dimensions, insufficient test precision and the like. The utility model provides a vector nozzle test board of a small turbojet engine for solving the technical problems. Disclosure of utility model The utility model aims to provide a small turbojet engine vector nozzle test bench, which aims to solve the defects of the traditional test bench when testing the small turbojet engine vector nozzle and improve the accuracy and reliability of the test. In order to achieve the purpose, the utility model provides the scheme that the vector spray pipe test board of the small turbojet engine comprises the following components: the fixed platform is used for fixing the equipment on the stable platform and bearing thrust; the base of the six-component balance is detachably arranged on the fixed platform and is used for measuring force and moment generated in the testing process of the turbojet engine; The working platform is fixedly arranged at the measuring end of the six-component balance and is used for transmitting the born force and moment to the six-component balance; The turbojet engine to be measured is sleeved in the fixing assembly in a hooped mode, an adjusting assembly is arranged on the fixing assembly, and the adjusting assembly is in butt joint with the outer wall of the turbojet engine. Preferably, the bottom end of the fixed platform is detachably connected with a fixing frame, and the fixed platform is fixed on the platform through the fixing frame. Preferably, the fixing component comprises a fixing base fixedly arranged on the working platform, a lifting fixing column is fixedly connected to the top end of the fixing base, a fixing ring for hooping the turbojet engine is fixedly connected to the top end of the fixing column, and the adjusting component is movably arranged on two sides of the fixing ring. Preferably, the fixed column comprises a fixed tube fixedly connected to the top end of the fixed base, the top end of the fixed tube is slidably connected with a movable column, and the top end of the movable column extends out of the fixed tube and is fixedly connected with the bottom end of the fixed ring. Preferably, the side wall of the fixed pipe is provided with a locking bolt, and the end part of the locking bolt stretches into the inner cavity of the fixed pipe and is in butt locking with the outer wall of the movable column. Preferably, the fixed ring comprises a first semi-ring fixedly connected to the top end of the movable column, a second semi-ring is hinged to one side of the first semi-ring, the free end of the second semi-ring is locked and connected through a locking buckle, and the turbojet engine is buckled between the first semi-ring and the second semi-ring. Preferably, the first half ring and the second half ring are provided with a plurality of heat dissipation holes for heat dissipation in a penetrating manner. Preferably, the adjusting assembly comprises a plurality of adjusting screws which are connected with the first semi-ring and the second semi-ring in a threaded mode, the adjusting screws extend into inner cavities of the first semi-ring and the second semi-ring, adjusting blocks are connected with the inner cavities of the first semi-ring and the second semi-ring in a rotating mode, and the adjusting blocks are abutted to the outer wall of the turbojet engine. Preferably, one side of the adjusting block, which is far away from the adjusting screw rod, is fixedly connected with a flexible contact pad, and the contact pad is abutted against the outer wall of the turbojet engine. Preferably, the inner walls of the first semi-ring and the second semi-ring are provided with a plurality of abdication grooves which are correspondingly arranged with the adjusting bloc