Gas-gas combustor support device for test

A technology of a bracket device and a combustion chamber, which is applied in the directions of jet propulsion devices, rocket engine devices, machines/engines, etc., can solve the problems of inconvenient replacement of gas-gas injectors, heavy engine weight, and difficulty in moving heavy engines. The effect of solving the difficulty of moving, reducing interference and convenient replacement

Inactive Publication Date: 2011-05-25
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

At present, in the support device of the gas combustion chamber used in the test, when replacing the gas injector, the body of the engine needs to be disassembled, and the weight of the engine is relatively heavy, so there are problems such as difficulty in moving the heavy engine and inconvenient replacement of the gas injector

Method used

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  • Gas-gas combustor support device for test
  • Gas-gas combustor support device for test
  • Gas-gas combustor support device for test

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Embodiment Construction

[0014] The present invention will be further described in detail with reference to the accompanying drawings and embodiments.

[0015] A kind of test gas combustion chamber support device of the present invention, as figure 1 As shown, it mainly includes: cement block 1, engine connecting frame 2, engine head 3, engine body 4, and engine support system 5. Described engine bracket system 5 mainly comprises rear bracket part 51 and front bracket part 52, as figure 1 As shown, the rear support part and the front support part are connected together by a load-bearing plate 16, and the rear support part and the front support part respectively have a pair of rolling bearings 14, and each pair of rolling bearings 14 is placed in the guide grooves provided at the center of two parallel guide rails 12 middle. The engine connection frame 2 is fixed on the cement block 1; the engine head 3 is installed on the connection frame 2; the engine body 4 is placed on the engine support system 5...

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Abstract

The invention provides a gas-gas combustor support device for test, which comprises a cement barrier platform, a connecting frame, an engine head part, an engine body part and an engine support system, wherein a front support part and a rear support part of the engine support system can be moved in guide rails through rolling bearings, the engine connecting frame is fixed on the cement barrier platform, the engine head part is arranged on the connecting frame, the engine body part is arranged on the front support part and the rear support part of the engine support system, and the engine headpart is connected with the engine body part through bolts. In the device provided by the invention, the engine body part can be disassembled through moving the rolling bearings of the support device,and then a multinozzle gas-gas injector assembly in the engine head part is convenient to replace. The invention solves the problem of difficulty in moving a heavy engine, and enables the multinozzlegas-gas injector assembly to be replaced conveniently.

Description

technical field [0001] The invention relates to a gas combustion chamber support device for a test, which belongs to the technical field of rocket engine tests. Background technique [0002] The injector is one of the key components of the liquid rocket engine, and the performance of the injector directly affects the performance of the engine. The full-flow afterburning cycle system is a new type of rocket engine cycle system. It is the staged combustion technology with the highest combustion performance at present, and it is one of the important development directions of liquid rocket engine technology. In the technical research of full-flow afterburning cycle engine, gas-gas combustion is one of the key technologies. All flow of hydrogen and oxygen is combusted once in the pre-combustion chamber to drive the turbine and then enters the combustion chamber for the second combustion. Therefore, the nozzle of the thrust chamber of the full-flow afterburning cycle engine is a ...

Claims

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Application Information

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IPC IPC(8): F02K9/96
Inventor 蔡国飙李茂高玉闪金平
Owner BEIHANG UNIV
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