Experimental study on methane heat transfer test system(PDF)
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
- Issue:
- 2013年04期
- Page:
- 19-23
- Research Field:
- 研究与设计
- Publishing date:
Info
- Title:
- Experimental study on methane heat transfer test system
- Author(s):
- GAO Xiang-yu; SUN Ji-guo; TIAN Yuan
- Beijing Aerospace Propulsion Institute, Beijing 100076, China
- Keywords:
- -
- PACS:
- V434-34
- DOI:
- -
- Abstract:
- A methane heat transfer test system was built to investigate the methane heat transfer and flow resistance characters in the coolant channel of thrust chamber in liquid rocket engine. Five supercritical hot fire tests and two subcritical hot fire tests for methane heat transfer study were performed in trust chamber extrusion heat test. The conditions of supercritical methane heat transfer tests are combustion chamber pressure of 5.5~7.5 MPa, O/H mixture ratio of about 6.8, methane temperature of 128~230 K, methane coolant mass flow of 5~7 kg/s, methane coolant inlet pressure of 8.3~11.7 MPa. The conditions of subcritical methane heat transfer tests are combustion chamber pressure of about 4 MPa, O/H mixture ratio of about 2.8, methane temperature of 128~189 K, methane coolant mass flow of about 2.9 kg/s, coolant inlet pressure of 3~3.5 MPa. The heat transfer and flow resistance characters of liq
Last Update: 1900-01-01