Solid-liquid rocket engine combustion chamber intermediate flow disturbing device

A solid-liquid rocket and spoiler technology, which is applied to rocket engine devices, machines/engines, jet propulsion devices, etc., can solve the problems of low combustion efficiency of solid-liquid rocket engines, achieve simple structure, clear and simple structure, and easy disassembly Effect

Inactive Publication Date: 2017-06-20
BEIHANG UNIV
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  • Application Information

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Problems solved by technology

Insufficient mixing of oxidant and fuel makes the combustion efficiency of solid-liquid rocket motors low. Common methods to increase the combustion efficiency of the engine include adding a spoiler to the

Method used

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  • Solid-liquid rocket engine combustion chamber intermediate flow disturbing device
  • Solid-liquid rocket engine combustion chamber intermediate flow disturbing device

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[0021] The present invention will be further described in detail below with reference to the drawings and embodiments.

[0022] The intermediate turbulence device of the combustion chamber of the solid-liquid rocket engine of the present invention includes a head cover 1, a panel 2, a front combustion chamber assembly 3, a combustion chamber flange 4, an insulation layer 5, a combustion chamber shell 6, a solid grain 7, and a turbulence The plate 8, the after-combustion chamber assembly 9, the rear head assembly 10, the nozzle plug cover 11, the nozzle fixing plate 12 and the nozzle assembly 13.

[0023] The front combustion chamber assembly 3 includes a front combustion chamber and a heat insulation layer of the front combustion chamber. The head cover 1, the panel 2, the front combustion chamber assembly 3, and the combustion chamber flange 4 are connected in sequence, fastened by bolts and sealed with an O-ring seal to ensure the air tightness and thermal protection requirements...

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Abstract

The invention discloses a solid-liquid rocket engine combustion chamber intermediate flow disturbing device. The solid-liquid rocket engine combustion chamber intermediate flow disturbing device is suitable for solid-liquid rocket engine ground hot firing test, is applied to a center single channel and adopts a single round hole powder charging solid-liquid rocket engine. A flow disturbing plate is a single-hole round ring, the thickness of the flow disturbing plate is 10-15 mm, the ratio of the hole diameter of the flow disturbing plate to the diameter of a grain channel is 0.5-0.6, and the flow disturbing plate is arranged in the position of the 70%-80% length of a combustion chamber, divides a grain into a front section of grain body and a back section of grain body, and is placed on the wall surface of a heat insulating layer of the combustion chamber and the end surface of the grain in a closely attached mode. The flow disturbing plate device is the round hole ring with the axis of the engine as the axis and is made of high-temperature-resistant high-silicon oxygen. According to the solid-liquid rocket engine combustion chamber intermediate flow disturbing device, the specific structure size and the position in the overall structure are given, the flow disturbing effect on fuel gas is achieved, and the requirements for the structural strength and heat protection of the flow disturbing device of the engine in the working process are met.

Description

technical field [0001] The invention relates to a spoiler in the middle of a combustion chamber of a solid-liquid rocket engine, which is suitable for the combustion chamber of the solid-liquid rocket engine with a single circular hole charge. Background technique [0002] The propellant of the solid-liquid rocket engine generally adopts a combination of liquid oxidizer and solid fuel, which has the advantages of good safety, good economy, easy shutdown and restart, and thrust adjustment. The oxidant of the solid-liquid rocket engine is injected into the combustion chamber through the pressurization system and then combusted with the solid fuel, so that the combustion process is characterized by typical diffusion combustion. Insufficient mixing of oxidant and fuel makes the combustion efficiency of solid-liquid rocket motors low. Common methods to increase the combustion efficiency of the engine include adding a spoiler to the grain, segmenting the charge, developing a high-...

Claims

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Application Information

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IPC IPC(8): F02K9/72F02K9/97
CPCF02K9/72F02K9/97
Inventor 田辉朱浩王中烁张源俊李承恩
Owner BEIHANG UNIV
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