Turbulence device for postcombustion chamber of hybrid rocket engine

A technology of engine and afterburner, which is applied in the field of spoiler device for afterburner of solid-liquid rocket engine, can solve the problems of increasing the difficulty of charge, changing the design form of the charge, etc., and achieve the effect of easy disassembly

Active Publication Date: 2013-02-27
BEIHANG UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Adding the spoiler structure to the grain requires changing the design of the grain and increasing the difficulty of charging

Method used

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  • Turbulence device for postcombustion chamber of hybrid rocket engine
  • Turbulence device for postcombustion chamber of hybrid rocket engine
  • Turbulence device for postcombustion chamber of hybrid rocket engine

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Embodiment Construction

[0011] The technical solution of the present invention will be further described below in conjunction with the accompanying drawings.

[0012] Such as figure 1 As shown, the spoiler device for the afterburner of the solid-liquid rocket engine provided by the present invention mainly includes the following components: a heat insulating layer 1 at the front of the spoiler, a heat insulating layer 2 at the rear of the spoiler, a metal frame 3 of the spoiler, and a rear part of the spoiler Combustion chamber housing 4, spoiler rear combustion chamber insulation layer 5, O-ring A6, O-ring B7, O-ring C8, bolt assembly A9, bolt assembly B10, combustion chamber housing 11, combustion chamber Heat insulation layer 12, engine charge 13, nozzle casing 14, nozzle heat insulation layer 15, nozzle throat liner 16.

[0013] Combustion chamber casing 11 and its internal combustion chamber insulation layer 12 and engine charge 13 form a combustion chamber assembly. Combustion chamber insulati...

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Abstract

The invention discloses a turbulence device for a postcombustion chamber of a hybrid rocket engine, which is suitable for ground heat run test of the hybrid rocket engine, is applied to a central single-channel hybrid rocket engine, but is not limited by specific propellant forms. The turbulence device comprises a combustion chamber component, a spoiler component, a spoiler postcombustion chamber component, a sealing and connecting component and a spray pipe component. The spoiler component and the spoiler postcombustion chamber component are combined into a whole so as to be connected with the spray pipe component through the sealing and connecting component and the spoiler postcombustion chamber component. The spoiler component consists of an internal metal spoiler and an external heat insulating structure, and spoiling holes are uniformly distributed in a circle taking the axis of the engine as the center. The spoiler component is used for realizing the turbulence function in gas in the central area, requirements on structural strength and thermal protection of the turbulence device can be satisfied during the working process of the engine, all the components are connected through a stepped fold line mode and O-shaped sealing ring connection, so that the requirements on airtightness and thermal protection are ensured during the working of the engine.

Description

【Technical field】 [0001] The invention relates to a turbulence device for an afterburner chamber of a solid-liquid rocket engine, which is suitable for the ground thermal test run test of the solid-liquid rocket engine. 【Background technique】 [0002] The solid-liquid rocket engine uses liquid oxidant and solid fuel as propellant, which has the advantages of good safety, good economy, easy shutdown and restart, and thrust adjustment. The oxidant of the solid-liquid rocket engine enters the combustion chamber through the injector through the pressurized delivery system, and burns with the solid fuel, which also determines that the combustion process presents the characteristics of typical diffusion combustion. Because the oxidant and fuel are not fully mixed before combustion, the unreacted oxidant and fuel are directly sprayed out of the nozzle, making the combustion efficiency of the solid-liquid rocket engine low, and adding a spoiler to the engine is to enhance the oxidiz...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/72
Inventor 田辉俞南嘉李新田曾鹏蔡国飙
Owner BEIHANG UNIV
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