Accession Number : ADA294772

Title :   Dimension-Optimizing Design Method For Annular-Type Cooling Channel Of Thrust Chamber,

Corporate Author : NATIONAL AIR INTELLIGENCE CENTER WRIGHT-PATTERSON AFB OH

Personal Author(s) : Chen, Jie

PDF Url : ADA294772

Report Date : 09 MAY 1995

Pagination or Media Count : 14

Abstract : The new-generation liquid oxygen/hydrocarbon propellant liquid fuel rocket engine will use a high-pressure combustion chamber arrangement. In this case, cooling the thrust chamber becomes a key technical problem. The article presents a design scheme for the geometric-dimension optimization of annular-type regenerative cooling channels. The aim of the optimization is minimum pressure losses as coolant passes through the cooling channel. As shown in typical computations and experiments, application of this optimizing design method can reduce 50% of pressure losses. In other words, the optimization design is advantageous in solving the cooling problem in high-pressure thrust chambers. jg

Descriptors :   *COOLING, *CHANNELS, *THRUST CHAMBERS, HEAT TRANSFER, OPTIMIZATION, COMPUTATIONS, SIZES(DIMENSIONS), HIGH PRESSURE, FUELS, HYDROCARBONS, PRESSURE, COMBUSTION CHAMBERS, REGENERATIVE COOLING, LIQUID PROPELLANTS, TRANSLATIONS, COOLANTS, LOSSES, DESIGN CRITERIA, ROCKET ENGINES, CHINA, CHINESE LANGUAGE, LIQUID OXYGEN, ANNULAR FLOW.

Subject Categories : Rockets
      Organic Chemistry
      Combustion and Ignition
      Liquid Propellant Rocket Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE