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Investigation on local overheating of the film cooling ring for LOX／kerosene high pressure chamber(PDF)

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

Issue:
2009年03期
Page:
11-14
Research Field:
研究与设计
Publishing date:

Info

Title:
Investigation on local overheating of the film cooling ring for LOX／kerosene high pressure chamber
Author(s):
Lti Fazhen91; Wu Haib01; Yang Yonghon91; Chi Chunz; Chen Jianhual
1 Xi'an Aerospace Propulsion Institute，Xi"an 710100，China； 2 Xi"all Space Engine Factory，Xi"an 710100，China
Keywords:
liquid rocket engine; thrust chamber; film cooling; heat transfer; ablation
PACS:
V434
DOI:
-
Abstract:
The multi-ring film cooling technique was introduced for thermal protection of the high pressure chamber of LOX／kerosene engine．The local overheating(even ablation)of the film cooling structure oceurred ocassionally at the slot step(aft lip)due to the high chamber pressure with large heat flux．The comparison analysis of heat transfer calculation was conducted，and the re— suits show that the hot-gas side wall temperature can reduce about 35 oC by increasing the flow rate by 25％and a lower peripheral mixture ratio．The measures of increasing film cooling flow rate，de— creasing peripheral mixture ratio and improving the local film ring structure aye effective for chamber wall thermal protection and preventing local overheating or ablation．

References:

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Last Update: 1900-01-01