|Table of Contents|

Performance research on turbine powder gas fleed system in liquid rocket engine(PDF)

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

Issue:
2008年06期
Page:
14-18
Research Field:
研究与设计
Publishing date:

Info

Title:
Performance research on turbine powder gas fleed system in liquid rocket engine
Author(s):
Li Yingqiang
Xi‘an Aerospace Propulsion Institute,Xi’an 710100,China
Keywords:
liquid rocket engineturbine nozzlepowder gas
PACS:
V434
DOI:
-
Abstract:
This article adopts the method of instantaneous pressure equilibrium of variational buming sud.ace of powder in solid mcket engine and now—rate equilibrium relation to calculate ex. actly the performance of powder gas in the front of the turbine nozzle.Various performance parame— ters of the powder gas in the front of the turbine nozzle were obtained.These parameters will be helpful to the research of turbine start and engine acceleration perfoHnances.

References:

[1]李宜敏,张中钦,赵元修.固体火箭发动机原理[M].北 京:国防工业出版社,1985.
[2]潘锦珊.气体动力学基础[M].北京:国防工业出版社,1986. [31武晓松,陈军,王栋.固体火箭发动机气体动力学[M].北 京:国防工业出版社.2005. [41王光林,蔡娥.固体火箭发动机设计[M].航空工业教材 编审室.1985.
[5]李伟民.液氧,煤油发动机试验起动过程推进剂供应技术 [J].火箭推进,2006,32(3):56—62。
[6]王鹏,李旭昌,徐颖军.同体火箭发动机总体优化设计 [J].火箭推进,2007,33(4):16—20.
[7]徐学文,王连生,牟俊林。某固体火箭发动机点火启动 过程三维流场一体化仿真[J].固体火箭技术,2008,31 (1):8—14.
[8]刘巍,杨涛,胡建新,等,气氧/酒精火炬式点火器试验 [J].推进技术,2008,29(3):269—273.
[9]郭K K,萨默菲尔德M.固体推进剂燃烧基础(下)[M]. 朱贵荣,于广经,廉茂林,等译。北京:宇航出版社, 1994.

Memo

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Last Update: 1900-01-01