Cold-state experimental simulation device and method for combustion stability boundary

By adding a cylindrical rod structure and adjusting the position of the rectifier grid in the coaxial dual centrifugal nozzle, the problem that the cold-state experiment could not simulate the combustion stability boundary was solved, and accurate simulation of combustion conditions was achieved, thus improving the accuracy of the experiment.

CN121007076BActive Publication Date: 2026-07-10XIAN 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
2025-09-29
Publication Date
2026-07-10

AI Technical Summary

Technical Problem

Existing technologies cannot effectively simulate the combustion stability boundary of coaxial dual centrifugal nozzles, and cold-state experiments cannot accurately reflect the stability characteristics under combustion conditions.

Method used

A cold-state experimental simulation device for combustion stability boundary was designed, including a nozzle, a rectifier grid, a simulated combustion chamber, a plate, and a pulsating pressure sensor. By adding a cylindrical rod structure in the inner nozzle and combining it with specific flow rate and position adjustments, the acoustic-vortex-combustion coupling process under combustion conditions is simulated.

Benefits of technology

Accurate cold-state simulation of the combustion stability boundary of coaxial dual centrifugal nozzles was achieved, suppressing the instability of the swirling vortex core flow, promoting the dominance of shear layer flow, and improving the accuracy of the simulation method.

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Abstract

The present application relates to a kind of combustion stability boundary cold-state experimental simulation device and method, belong to liquid rocket engine combustion chamber experimental simulation technical field, solve the technical problem that coaxial double centrifugal nozzle combustion stability boundary cold-state experiment cannot simulate, its device includes nozzle, rectifier grid, simulated combustion chamber, flat plate, pulsating pressure sensor.Simulated combustion chamber is located on the flat plate placed horizontally, rectifier grid is located in simulated combustion chamber downstream of nozzle, nozzle is fixed on flat plate, pulsating pressure sensor is installed on the side wall of simulated combustion chamber.The method includes calculating nitrogen mass flow, determining the best position of rectifier grid;Fixed rectifier grid best position, determine the steps of stability boundary.The present application is used for liquid rocket engine combustion chamber combustion unstable boundary determination cold-state experiment.
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