Film Cooling in a High-Pressure Subscale Combustion Chamber

By the application of film cooling in addition to regenerative cooling, a considerable reduction in thermal and structural loads of rocket combustion-chamber walls can be reached. This paper discusses important influence parameters on film cooling in terms of efficiency of the injected film and wall temperature reduction. For the experimental investigations a high-pressure subscale combustion chamber operated with the cryogenic propellant combination LOX=GH2 was used. A gaseous film with ambient tempered hydrogen was injected in the axial direction at the face plate. Typical film-cooling parameters such as film blowing rate, velocity ratio between film injection velocity and hot-gas velocity, circumferential slot positioning, and film injection slot height were investigated systematically at the European Research and Technology Test Facility P8.

[1]  Michael Oschwald,et al.  Einfluss der Temperaturabhängigkeit der Materialeigenschaften auf den Wärmehaushalt in regenerativ gekühlten Brennkammern , 2004 .

[2]  J. G. Lucas,et al.  AN EXPERIMENTAL INVESTIGATION OF GASEOUS-FILM COOLING OF A ROCKET MOTOR , 1963 .

[3]  Richard J Goldstein,et al.  Row-of-holes film cooling of curved walls at low injection angles , 1997 .

[4]  J. L. Stollery,et al.  On the use of a boundary-layer model for correlating film cooling data , 1967 .

[5]  Jon Volkmann,et al.  Gas side heat flux and film coolant investigation for advanced LOX/hydrocarbon thrust chambers , 1990 .

[6]  Dmitry Suslov,et al.  Film Cooling of Accelerated Flow in a Subscale Combustion Chamber , 2009 .

[7]  O. Haidn,et al.  P8 : The new French/German test facility for H2/O2 high pressure rocket engine combustion research , 1998 .

[8]  Richard J Goldstein,et al.  Film cooling downstream of a row of discrete holes with compound angle , 2000 .

[9]  Sylvain Guedron,et al.  Vulcain X technological demonstration roadmap , 2006 .

[10]  David H. Huang,et al.  Modern Engineering for Design of Liquid Propellant Rocket Engines , 1992 .

[11]  Richard J Goldstein,et al.  Film Cooling With Normal Injection Into a Supersonic Flow , 1968 .

[12]  Gus J. Caras,et al.  TRANSPIRATION AND FILM COOLING OF LIQUID ROCKET NOZZLES , 1966 .

[13]  Scott Claflin,et al.  Investigation of throat film coolant for advanced LOX/RP-1 thrust chambers , 1991 .

[14]  Dmitry Suslov,et al.  Convective and Film Cooled Nozzle Extension for a High Pressure Rocket Subscale Combustion Chamber , 2010 .

[15]  George P. Sutton,et al.  History of liquid propellant rocket engines in the United States , 2003 .

[16]  Dmitry Suslov,et al.  Circumferential Film Cooling Effectiveness in a LOX/H2 Subscale Combustion Chamber , 2009 .

[17]  Dmitry Suslov,et al.  Measurement Techiques for te Investigation of Heat Transfer Processes at the European Research and Technology Test Facility P8 , 2005 .

[18]  Dmitry Suslov,et al.  Experimental Investigation of Film Cooling with Tangential Slot Injection in a LOX/CH4 Subscale Rocket Combustion Chamber , 2009 .

[19]  Richard J Goldstein,et al.  Film cooling with helium injection into an incompressible air flow , 1966 .

[20]  Bernhard Weigand,et al.  Circumferential Behavior of Tangential Film Cooling and Injector Wall Compatibility in a High Pressure LOX/GH2 Subscale Combustion Chamber , 2008 .

[21]  J. L. Stollery,et al.  The influence of foreign gas injection and slot geometry on film cooling effectiveness , 1969 .

[22]  Phillip M. Ligrani,et al.  Heat transfer, adiabatic effectiveness, and injectant distributions downstream of a single row and two staggered rows of compound angle film-cooling holes , 1992 .

[23]  Michael Oschwald,et al.  Test Specimen Design and Measurement Technique for Investigation of Heat Transfer Processes in Cooling Channels of Rocket Engines under Real Thermal Conditions , 2003 .

[24]  Shinji Honami,et al.  Behavior of the Laterally Injected Jet in Film Cooling: Measurements of Surface Temperature and Velocity/Temperature Field Within the Jet , 1994 .

[25]  K. Fröhlke,et al.  FIRST HOT FIRE TEST CAMPAIGN AT THE FRENCH/GERMAN RESEARCH FACILITY P8 , 1997 .

[26]  Oskar Haidn,et al.  Influence Parameters on Film Cooling Effectiveness in a High Pressure Subscale Combustion Chamber , 2009 .

[27]  Bernhard Weigand,et al.  Investigation of Film Cooling in a High Pressure LOX/GH2 Subscale Combustion Chamber , 2008 .

[28]  S. Papell,et al.  Effect on Gaseous Film Cooling of Coolant Injection Through Angled Slots and Normal Holes , 1960 .

[29]  Richard J Goldstein,et al.  Film cooling with air and helium injection through a rearward-facingslot into a supersonic air flow. , 1966 .

[30]  George P. Sutton,et al.  History of Liquid-Propellant Rocket Engines in Russia, Formerly the Soviet Union , 2003 .

[31]  Richard Arnold.  Experimentelle Untersuchungen zur Filmkühlung in Raketenbrennkammern , 2008 .

[32]  J. Whitelaw,et al.  Convective heat and mass transfer , 1966 .

[33]  George P. Sutton,et al.  History of Liquid Propellant Rocket Engines , 2005 .

[34]  Patrice Fayolle,et al.  VULCAIN X Technological Demonstration Roadmap , 2006 .