关键词: 液体推进剂火箭发动机;推力燃烧室;热力学循环;传热;试验;数值仿真

Abstract: A single-injector heat-sink chamber was designed and hot-fire tested for 17 times at chamber pressure from 0.92 MPa to 6.1 MPa,and wall temperature measurement method was used to get the heat flux distributions on the inner wall along with the axial direction of the chamber.The convection heat fluxes were separated from the total heat fluxes to identify the relationship between the convection heat flux and corresponding chamber pressure.Single-injector chamber flows were also simulated with multi-species turbulence N-S equations at higher chamber pressure from 5 MPa to 20 MPa.Chemical reaction was modeled with Arrhenius formulation.Detailed 9 steps chemical mechanism was used to describe the reaction of hydrogen and oxygen.Both the flows structures and heat flux profiles on inner wall were obtained and discussed,and the results of ex-periments and calculations indicated the same trend.

Key words: Liquid propellant rocket engine;Thrust chamber;Thermodynamic cycle;Heat transfer;Experiment;Nu-merical simulation