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Ground thrust vector calibration device for small turbojet engine

A turbojet engine and thrust vectoring technology, which is applied in the field of wind tunnel tests, can solve the problems that the large-angle deflection of the tail nozzle cannot be realized, and the influence of the temperature of the exhaust flame of the turbine engine is not considered, so as to facilitate processing and assembly, reduce influence, and reduce transmission. hot effect

Active Publication Date: 2022-05-10
LOW SPEED AERODYNAMIC INST OF CHINESE AERODYNAMIC RES & DEV CENT
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  • Abstract
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  • Application Information

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Problems solved by technology

[0002] Part of the power model in the wind tunnel test uses a power system with a small turbojet engine with a thrust vectoring tail nozzle embedded in it. Before the test, it is necessary to calibrate the power of the engine with a tail nozzle and the thrust vectoring device. The deflection range of the thrust vectoring nozzle is up to 90° , and the exhaust flame temperature of the turbojet engine is about 600-700°C, the existing test bench (such as patent CN201810305020.8) cannot achieve a large angle deflection of the exhaust nozzle, and does not consider the influence of the exhaust flame temperature of the turbine engine on the exhaust nozzle

Method used

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  • Ground thrust vector calibration device for small turbojet engine
  • Ground thrust vector calibration device for small turbojet engine
  • Ground thrust vector calibration device for small turbojet engine

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Embodiment Construction

[0027] The following description provides many different embodiments, or examples, for implementing various features of the invention. The elements and arrangements described in the following specific examples are only used to express the present invention in a concise manner, and are only used as examples rather than limiting the present invention.

[0028] A small turbojet engine ground thrust vector calibration device, such as figure 1 and figure 2 As shown, it includes a deflector 01, and the deflector 01 includes a deflector and a deflector base 011; the deflector base 011 is fixed at the tail end of the nozzle diffuser section 02, the The deflector is rotatably connected to the deflector base 011 , and the rotation angle of the deflector is adjusted by rotating the positioning connector 016 .

[0029] Further, in this embodiment, the deflector includes an upper deflector 012, a lower deflector 013, a left deflector 014 and a right deflector 015; the deflector base 011...

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Abstract

The invention is suitable for the technical field of wind tunnel tests, and provides a small turbojet engine ground thrust vector calibration device, which comprises a flow guide part, and is characterized in that the flow guide part comprises a flow guide plate and a flow guide plate base; the flow guide plate base is fixed to the tail end of the spray pipe diffusion section, the flow guide plate is rotationally connected to the flow guide plate base, and the rotating angle of the flow guide plate is adjusted by rotating the positioning connecting piece. The guide plate is arranged at the tail end of the nozzle diffusion section, and the rotating angle of the guide plate can be adjusted by rotating the connecting piece, so that the upper guide plate and the lower guide plate of the thrust vector nozzle deflect within the range of more than 90 degrees, and the left guide plate and the right guide plate deflect within the range of + / -30 degrees; the spray pipe diffusion section, the flow guide part and the rotary positioning connecting piece are all arranged to be of a steel structure, the high temperature of the tail flame of the turbine engine can be borne, and the testing device cannot be affected by the high temperature of the tail flame of the turbine engine.

Description

technical field [0001] The invention relates to the technical field of wind tunnel tests, in particular to a ground thrust vector calibration device for a small turbojet engine. Background technique [0002] Part of the power model in the wind tunnel test uses a power system with a built-in small turbojet engine and a thrust vectoring tail nozzle. Before the test, it is necessary to calibrate the power of the engine with a tail nozzle and the thrust vectoring device. The deflection range of the thrust vectoring nozzle is up to 90° , and the exhaust flame temperature of the turbojet engine is about 600-700°C, the existing test bench (such as patent CN201810305020.8) cannot achieve a large angle deflection of the exhaust nozzle, and does not consider the influence of the exhaust flame temperature of the turbine engine on the exhaust nozzle. Contents of the invention [0003] The purpose of this invention is to provide a kind of high temperature resistant device that can carr...

Claims

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Application Information

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IPC IPC(8): G01M15/14G01L5/12G01M9/04
CPCG01M15/14G01L5/12G01M9/04Y02T50/60
Inventor 蒋永任忠才张磊郭天豪聂博文张海酉岑飞朱任宇梁勇
Owner LOW SPEED AERODYNAMIC INST OF CHINESE AERODYNAMIC RES & DEV CENT
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