Accession Number : ADA316770
Title : Analysis of the Effect of Liquid Film Cooling on the Performance of the Two-Component Attitude Control Engine,
Corporate Author : NATIONAL AIR INTELLIGENCE CENTER WRIGHT-PATTERSON AFB OH
Personal Author(s) : Ping, Li ; Yinfang, Wang
PDF Url : ADA316770
Report Date : 30 SEP 1996
Pagination or Media Count : 21
Abstract : By analyzing the operational characteristics of liquid film/radiation cooling of a two-component attitude control engine based on the swirling suction models of two side-zone flow pipes, the authors of this paper divided the combustion chamber flow field approximately into one central zone and two side zones, and calculated the effect of the liquid film cooling of the liquid film/radiation cooling low-thrust liquid rocket engine on its performance loss. Also discussed are the performance analysis results together with the selection of the engine design parameters for an integrated thermal conductivity model. The method presented in this paper can be regarded as a reference for performance calculation and parameter optimization in the design of similar engines.
Descriptors : *ENGINES, RADIATION, INTEGRATED SYSTEMS, OPTIMIZATION, ATTITUDE CONTROL SYSTEMS, COMPUTATIONS, PERFORMANCE TESTS, PARAMETERS, FLOW FIELDS, THERMAL CONDUCTIVITY, COMBUSTION CHAMBERS, LOSSES, SIDES, SUCTION, FILM COOLING, CHINA, CHINESE LANGUAGE, LIQUID COOLING.
Subject Categories : Jet and Gas Turbine Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE