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The effect of initial LOX／GH2 liquid rocket hydrogen temperature on engine combustion lnstability (PDF)

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

Issue:
2009年01期
Page:
27-30
Research Field:
研究与设计
Publishing date:

Info

Title:
The effect of initial LOX／GH2 liquid rocket hydrogen temperature on engine combustion lnstability
Author(s):
Cheng Yufeng1; Nie Wansheng2; Feng Songjiang1
1 Department of Postgraduate，the Academy of Equipment Command＆Technology，Beijing 101416，China； 2 Department of Space Equipment,the Academy of Equipment Command＆Technology，Beijing 101416，China
Keywords:
hydrogen-oxygen rocket engine; combustion instability; numerical simulation
PACS:
V434.1
DOI:
-
Abstract:
The combustion instability in one LOX／GH2 liquid rocket engine was studied by USing CFD methods．The effects of initial hydrogen temperature on combustion oscillation at different operational conditions were studied，and the roles of instable pressure frequencies and the combus— tion stability limiting map are developed．Results show that combustion instability will happened at a specific initial hydrogen temperature bound and the upper limit of this initial hydrogen temperature bound will increases鹄the O／F increases．In addition．the instable dominant frequencies age present as multiple frequencies and have a maximum value at a hydrogen temperature bound from 70 K to 110 K．

References:

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Last Update: 1900-01-01