|Table of Contents|

Numerical simulation of non-uniform circular-hole film cooling at the near-injection region of hydrogen/oxygen rocket engine(PDF)

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

Issue:
2022年04期
Page:
1-12
Research Field:
目次
Publishing date:

Info

Title:
Numerical simulation of non-uniform circular-hole film cooling at the near-injection region of hydrogen/oxygen rocket engine
Author(s):
WANG Taiping1;  SUN Bing2;  XUE Lipeng1;  LIU Di3;  LI Lin1
(1.Beijing Key Laboratory of Cryogenic Technology Research, Beijing Institute of Astronautical Systems Engineering, Beijing 100076, China2.Beihang University, Beijing 100084, China 3.Beijing Electro-Mechanical Engineering Institute, Beijing 100074, China)
Keywords:
head gas film cooling non-uniform film film cooling efficiency combustion chamber hydrogen/oxygen rocket engine
PACS:
V434
DOI:
-
Abstract:
The thermal environment of the combustion chamber wall in hydrogen/oxygen rocket engine is very harsh, and the circular-hole film cooling is one of the main auxiliary methods to reduce the heat load in the near-injection region.In this study,the three-dimensional numerical simulation of the head gas film with cylindrical film hole was carried out, considering the influence of regenerative cooling outside the thrust chamber.Through comprehensive numerical experiments, the effects of parameters such as the proportion of gas film flow ratio, the diameter of film hole and the area ratio of adjacent film holes, and a gas film cooling scheme of circular hole head with non-uniform distribution was proposed.The results show that there is an optimal blowing ratio to make the cooling effect of the head area the best in the film cooling of the head of the hydrogen/oxygen rocket engine.The optimal blowing ratio is determined by the ratio of the air film flow rate and the diameter of the air film hole, and the optimal air blowing ratio in this study is between 5.454 and 5.849.Through the reasonable structure design of the non-uniform circular-hole, the area ratio of adjacent gas film holes is controlled within the range of 0.6-0.8.The proposed non-uniform film hole scheme is beneficial to the improvement of the overall combustion chamber performance, which can provide a reference for engineering design.

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