Research on gas film cooling at nozzle extension section of thrust chamber for upper stage engine(PDF)
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
- Issue:
- 2013年04期
- Page:
- 13-18
- Research Field:
- 研究与设计
- Publishing date:
Info
- Title:
- Research on gas film cooling at nozzle extension section of thrust chamber for upper stage engine
- Author(s):
- SUN Yong-qi; LI Bao-rong; YANG Jian-wen
- Xi’an Aerospace Propulsion Institute, Xi’an 710100, China
- Keywords:
- liquid rocket engine; thrust chamber; nozzle extension section; gas
- PACS:
- V434-34
- DOI:
- -
- Abstract:
- Nitrogen tetroxide (N2O4)/unsymmetrical dimethylhydrazine (UDMH) is adopted as propellant of the upper stage engine. The turbine exhaust gas is imported into the nozzle extension section of thrust chamber to form low temperature gas film. The simulation calculation and the ground hot-firing test were performed to validate the cooling method. The results show that the pressure of the main gas from the thrust chamber is equal with that of the turbine exhaust gas, and the gas film formed by the turbine exhaust gas which flows along the nozzle extension section and appresses with the inner wall of the nozzle has no perturbation to the main gas, and protects the nozzle extension section from high temperature. The value of heat-transfer calculation of the nozzle extension section of thrust chamber coincides with that of temperature detection during the ground hot-firing test. The pressure in the exhaust gas collector is basically uniform. It satisfied the requirements of a project.
Last Update: 1900-01-01