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3) combustion chamber process characteristics: pressure; main flow
temperature; main flow turbulence intensity; boundary layer thickness;
4) parameters of the film and main flow combined: relative mass loading
of the injected and the main flow
M
.
It should also be noted that some of these factors are studied quite well,
while others require the further study.
The following guidelines with regard to the film cooling of the LTRE
combustion chamber can be given:
1) relative mass loading of the injected and the main flows
M
should
be close to a unity;
2) the coolant should be injected along the combustion chamber wall
(the coolant injection angle equals zero);
3) coolant injection slots should be positioned between the periphery
injectors;
4) the main flow should be organized so that it was maximally laminar
(the main flow turbulence intensity should be as low as possible).
REFERENCES
[1] Alemasov V.E., Dregalin A.F., Tishin A.P., Khudyakov V.A., Kostin V.N.,
Glushko V.P. eds. Termodinamicheskie i teplofizicheskie svoystva produktov
sgoraniya. Tom 6: Topliva na osnove perekisi vodoroda. [Thermodynamic and
thermal-physical property properties of fire gases. Vol. 6. Fuels based on hydrogen
peroxide]. Moscow, VINITI AN SSSR Publ., 1973. 528 p.
[2] Alemasov V.E., Dregalin A.F., Tishin A.P., Khudyakov V.A., Kostin V.N.,
Glushko V.P., eds. Termodinamicheskie i teplofizicheskie svoystva produktov
sgoraniya. Tom 2: Topliva na osnove perekisi kisloroda [Thermodynamic and
thermal-physical property properties of fire gases. Vol. 6. Fuels based on oxygen.].
Moscow, VINITI AN SSSR Publ., 1973. 489 p.
[3] Ponomarenko A.
RPA:
Tool
for Rocket
Propulsion Analysis.
Thermal
Analysis of
Thrust
Chambers,
2012.
Available at:
http://propulsionanalysis.com/downloads/2/docs/RPA_ThermalAnalysis.pdf(accessed 16.04.2013).
[4] Veyalis S.A., Serpionova A.P., Linenko S.P. Film cooling. Gaseous film cooling.
Overview of international papers on Russian and foreign content press for 1957–
1977 years. GONTI-8 [State department of scientific and technical information],
1979, ser. IV, no. 41 (64), pp. 1–84 (in Russ.).
[5] Volchkov E.P. Pristennye gazovye zavesy [Wall-mounted gaseous film]. Novosibirsk,
Nauka Publ., 1983. 240 p.
[6] Arnold R., Suslov D.I., Haidn O.J. Film Cooling in a High-Pressure Subscale
Combustion Chamber. Journal of Propulsion and Rocket. 2010. Vol. 26, no. 5,
pp. 428–438.
[7] Druzhin A.N. Thermal and energy efficiency of sub- and supersonic gaseous film in
rocket engine with small propulsion.
Diss. kand. tekhn. nauk
[Cand. tech. sci. diss.].
Samara, 2002. 213 p.
[8] Arnold R., Suslov D.I., Haidn O.J. Experimental Investigation of Film Cooling with
Tangential Slot Injection in a LOX/CH
4
Subscale Rocket Combustion Chamber.
Trans. JSASS Space Tech.
, Japan, vol. 7, 2009.
88 ISSN 0236-3941. HERALD of the BMSTU. Series “Mechanical Engineering”. 2014. No. 1