A system and method for verifying the adaptability of engine ignition shock wave environment in confined space

Abstract

The invention belongs to the field of liquid rocket engine design, is suitable for a liquid rocket engine with an ignition plume shock wave environment in a confined space, and relates to a system and method for verifying the adaptability of an engine to an ignition plume shock wave environment in a confined space. When verifying the adaptability of the engine's confined space ignition shock wave environment, the liquid rocket engine is in the test state of a stand-alone hot test run. A baffle is set up in the downstream of the engine nozzle according to the boundary conditions of the confined space to simulate the working environment of the engine's confined space ignition. After simulating the ignition time in the confined space, turn off the engine to complete the verification, or remove or move the baffle to keep the engine out of the confined space and continue the normal ignition verification of the engine after experiencing the shock wave environment. The actual residence time of the shock wave in the nozzle is determined by the thrust parameter. It overcomes the difficulty and low accuracy of using flow field and heat transfer simulation technology to determine the shock wave environment parameters inside the nozzle, and provides an accurate basis for the shock wave environment adaptability of liquid rocket engines.

Description

technical field [0001] The invention belongs to the field of liquid rocket engine design, and is suitable for liquid rocket engines with an ignition plume shock wave environment in a confined space, and in particular relates to a system and method for verifying the adaptability of an engine in a confined space ignition shock wave environment. Background technique [0002] Liquid rocket engine nozzles usually ignite and work in an open environment, but when the supersonic flow at the outlet of the nozzle is blocked, a shock wave will be generated at the front of the obstacle, and when the distance between the nozzle and the obstacle is small enough, it will A normal shock wave is formed inside the nozzle, so that the wall temperature of the nozzle wall near the wall of the shock wave will rise rapidly. When the temperature exceeds the temperature resistance limit or high temperature strength limit of the nozzle wall, the nozzle will be burned or destroyed. [0003] At present...

AI Technical Summary

Problems solved by technology

[0004] In order to overcome the difficulty and low accuracy of using flow field and heat transfer simulation technology to determine the parameters of the shock wave environment inside the nozzle, the present invention proposes a system and method for verifying the adaptability of the ignition shock wave environment in a confined space of the engine. In real ignition, the environment where the shock wave resides in the nozzle is simulated, and the adaptability and adaptive boundary of the liquid rocket engine to this working environment are verified. Compared with the simulation technology, the measurement is simpler and the judgment is more accurate , providing a more reliable basis for the adaptability of liquid rocket engines to shock wave environments

Images