Solid-liquid rocket engine combustion chamber intermediate flow disturbing device

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-...

AI Technical Summary

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 grain, segmenting the charge, developing a high-efficiency combustion injector, and rationally designing Drug shape, etc., adding a turbulence device can be said to be a relatively easy method to implement

Images