|Table of Contents|

Structure pattern analysis of gas-gas inj ector(PDF)

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]

Issue:
2009年03期
Page:
6-10
Research Field:
研究与设计
Publishing date:

Info

Title:
Structure pattern analysis of gas-gas inj ector
Author(s):
Du ZhenggangGao YushanCai Guobiao
College of Astronautics,Beijing University of Aeronautics and Astronautics,Beijing 100083,China
Keywords:
injectordouble shear coaxialflow rateefficiency
PACS:
V434
DOI:
-
Abstract:
The shear coaxial,swirl coaxial and double shear coaxial injector using the gaseous oxygen and hydrogen as propellants were designed to analyse its geometrical dimension.The reacting flow field in chambers of shear coaxial and double shear coaxial injector were simulated in combina· tion with the two equation k- tturbulence model to investigate the effect of mass flow rate and injector pattern on the combusting process.The results displayed that the structure of shear coaxial in— jector was simple;the small discharge coefficient as well as the swirl chamber made the outline size of swirl injector much bigger;the double shear coaxial injector created double flame fronts in the chamber and achieving high combustion efficiency at the condition of large mass flow rate.

References:

[1]Farhangi S,Yu T,aojas L,et a1.Gas—Gas Injector Technology for Full Flow Combustion Cycle Application [R].AIAA 99—2757.
[2]Calhoon D J,Ito Kom.Investigation of Gaseous Propellant Combustion and Associated Injector—Chamber design Guidelines[R].Aerojet Liquid Rocket Company,NASA CR一121234,Contract NAS3—13379,July 1973.
[3]Foust M J'Pal s,Santoro R J.Gaseous Propellant Rocket Studies Using Raman Peetroseopy[R].ne Pennsylvania State University Park.PA 1 6802 AlAA 96-2766.
[4]Jones R A,W de Groot.Oxygen Temperature and Concentration Measurements in H2-102.Rocket Engines [R].AlAA 96-0439.
[5]Foumet A,Lonchard J M,Thomas J L.Technological Demonstration for Low Cost Gas Generator[R].AIAA 2004--4006.
[6]萨顿G P,比布拉兹0.火箭发动机设计基础[M].北京: 科学出版社.2003.
[7]中国航天工业总公司.世界导弹与航天发动机大全[M]. 北京:军事科学出版社.1999.
[8]王建,孙冰,魏玉坤.气膜冷却传热传质类比研究[J].火 箭推进,2008,34(2):31—36.
[9]YangVigorLiquidRocketEngineThrustChamberAspectsof Modeling,Analysis,and Design [M].Virginia:American Institute of aeronautics and astronautics.2004.
[10]黄兵,张楠,液体火箭发动机初始雾化液滴分布预测[J]. 火箭推进,2007,33(2):31—39.

Memo

Memo:
-
Last Update: 1900-01-01