基于简谐喉部的燃烧室压力自振荡实验装置及方法

By designing a combustion chamber pressure self-oscillation experimental device with a harmonic throat, and using an elastic component in contact with the combustion chamber outlet to excite spontaneous pressure oscillation, the problem of large error in injector stability testing in the prior art is solved, and high-precision injector stability assessment is achieved.

CN117030271BActive Publication Date: 2026-07-17XIAN AEROSPACE PROPULSION INST
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
XIAN AEROSPACE PROPULSION INST
Filing Date
2023-06-14
Publication Date
2026-07-17

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Abstract

本发明提供一种基于简谐喉部的燃烧室压力自振荡实验装置及方法，用于解决现有的喷注器稳定性测试方法测量误差较大、准确性较低的技术问题。本发明的实验装置包括装置本体和设置于装置本体内的弹性组件；装置本体包括出口底盘、安装底盘及连接出口底盘和安装底盘的多个连接杆；弹性组件位于出口底盘和安装底盘之间，多个连接杆均布于弹性组件外的周向；出口底盘上设有通孔；弹性组件包括依次连接的堵盖，至少一个弹簧，以及弹簧底座，其中，堵盖靠近出口底盘的内侧，燃烧室的出口端穿过通孔与堵盖的外侧面接触；弹簧底座与安装底盘连接。
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