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A Method of Actively Adjusting Engine Nozzle Damping to Suppress Unstable Combustion

A technology for engine nozzles and stable combustion, which is applied in the direction of machines/engines, jet propulsion devices, etc., can solve the problems of prolonging the research cycle and increasing funds, and achieve the effect of reducing risks and prolonging the development cycle

Inactive Publication Date: 2017-09-15
BEIJING INSTITUTE OF TECHNOLOGYGY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

It often leads to the extension of the research cycle and a large amount of additional funds

Method used

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  • A Method of Actively Adjusting Engine Nozzle Damping to Suppress Unstable Combustion
  • A Method of Actively Adjusting Engine Nozzle Damping to Suppress Unstable Combustion
  • A Method of Actively Adjusting Engine Nozzle Damping to Suppress Unstable Combustion

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Effect test

Embodiment 1

[0039] Such as figure 1 , figure 2 As shown, a method of actively adjusting the nozzle damping of a rocket engine to suppress unstable combustion in this embodiment adopts the single-two-time flow nozzle injection method in the converging section, including the engine nozzle 1, the screw washer 2, the jet injection device 3, Bolt 4, converging section connecting piece 5, end face rear sealing O-ring 6, nut 7, air collecting chamber connecting piece 8, installation and dismounting screw 9, air collecting chamber 10, bolt gasket 11, detachable converging section 12, side A sealing O-ring 13 and a front sealing O-ring 14 on the end face.

[0040] The detachable convergent section has a convergent half angle of 50 degrees and a nozzle expansion ratio of 3.5. The secondary flow nozzle is sprayed perpendicular to the side of the convergent section at a 90-degree angle, and is mutually excited at a 40-degree angle with the main flow. Evenly distributed secondary flow nozzles are ...

Embodiment 2

[0045] Such as image 3 As shown, a method of actively adjusting the damping of the rocket engine nozzle to suppress unstable combustion in this embodiment adopts the bi-weekly secondary flow nozzle injection method in the converging section, including the engine nozzle 1, the screw gasket 2, the jet injection device 3, Bolt 4, converging section connecting piece 5, end face rear sealing O-ring 6, nut 7, air collecting chamber connecting piece 8, installation and dismounting screw 9, air collecting chamber 10, bolt gasket 11, detachable converging section 12, side A sealing O-ring 13 and a front sealing O-ring 14 on the end face.

[0046] The detachable convergent section has a convergent half angle of 50 degrees and a nozzle expansion ratio of 3.5. The secondary flow nozzle is sprayed perpendicular to the side of the convergent section at a 90-degree angle, and is mutually excited at a 40-degree angle with the main flow. Evenly distributed secondary flow nozzles are set at ...

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Abstract

The invention discloses a method for actively adjusting damping of an engine jet pipe to restrain unstable combustion, and belongs to the field of a rocket engine with adjustable damping of a jet pipe. The method for applying secondary flow to the tail end of a contraction section of a jet pipe is adopted, so that main flow and the secondary flow interfere with each other; the secondary flow adopts liquid-phase working media and is atomized or is in chemical reaction with the main flow, and then distribution of atomized droplets or reaction products can absorb acoustic energy in the main flow, damping of the jet pipe is increased and accordingly unstable combustion is restrained; and by changing the secondary flow and the jet mode, the damping of the jet pipe of the rocket engine can be adjusted as needed. The method greatly reduces the possibility of abnormal work or even explosion of the engine during a ground firing test, so that in the designing and testing process of the solid rocket engine, the development period is shortened, and the project funding is saved.

Description

technical field [0001] The invention discloses a method for suppressing unstable combustion by actively adjusting nozzle damping of a rocket engine, relates to a method for reducing pressure oscillation in a combustion chamber by interfering with a main flow of a secondary jet, and belongs to the field of rocket engines with adjustable nozzle damping. Background technique [0002] Unstable combustion is also called oscillating combustion of the engine. Its basic feature is that the pressure in the combustion chamber changes periodically with time. When the pressure amplitude is large, the internal ballistic curve of the engine will also undergo irregular changes such as the increase or jump of the average pressure, which will make the expected thrust scheme impossible to achieve. Excessive pressure peaks can also compromise the structural integrity of the engine, leading to catastrophic failures. Not only that, the pressure oscillation will also cause thrust oscillation an...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02K1/78
CPCF02K1/78
Inventor 曾海波谢侃郭常超岳明辉王宁飞
Owner BEIJING INSTITUTE OF TECHNOLOGYGY