Experimental and Numerical Film Cooling Investigations in a GOX/ Kerosene Rocket Combustion Chamber

Schlieben, Gregor; Kirchberger, Christoph; Haidn, Oskar; Höglauer, C.; Kniesner, Björn; Knab, O.

doi:10.2514/6.2014-4008

Cited by 1 publication

(2 citation statements)

References 4 publications

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“…ATLLAS, coordinated by ESA-ESTEC, is supported by the EU within the 6th Framework Programme Priority 1. 4 …”

Section: Acknowledgmentsmentioning

confidence: 97%

“…pressures higher 2.34 MPa but inlet temperatures well below 684.3 K, this is a potential source for error in modeling. Nevertheless, gaseous film models usually yield too low cooling efficiencies compared to test data in the past 4,5 . Therefore, the application of liquid film modeling approaches will be on focus in the following section.…”

Section: B Film Models In Open Literaturementioning

confidence: 98%

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Assessment of Analytical Models for Film Cooling in a Hydrocarbon/GOX Rocket Combustion Chamber

Kirchberger¹,

Schlieben²,

Haidn³

2012

48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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The understanding of the mechanisms of heat transfer and advanced cooling techniques is a key for mastering the designing of reliable and efficient rocket combustion chambers. However, the effects determining film cooling efficiency as well as influences on the combustion process itself under typical conditions for rocket engines are still insufficiently understood. Therefore, the Institute for Flight Propulsion (LFA) of the Technische Universität München operates a rocket combustor test facility which allows testing at application-relevant conditions. The experimental work is complemented by numerical investigations, where in day-to-day operations also analytical and semi-empirical correlations are used. This paper presents an assessment of different analytical and semiempirical film cooling models known from open literature and their application to kerosene film cooling in a GOX/ kerosene combustion chamber. Nomenclature AcronymsCC = Combustion chamber CFD = Computational Fluid Dynamics GOX = Gaseous oxygen MR = Mixture ratio (here oxygen/kerosene mass flow ratio) NHFR = Net Heat Flux Reduction (cooling effectiveness) THERMTEST = Tool for thermal simulation of rocket combustion chamber by TUM Greek Letters  = heat transfer coefficient  = adiabatic film cooling effectiveness,     c cool c aw T T T x T x      = film part, relative film mass flow,  Injector , Kerosene Film Film m m / m       Latin Letters Indices m  = mass flow rate aw = adiabatic wall p = pressure c = chamber, core stream T = temperature cool = coolant (esp. film) O/F = mixture ratio e = entrainment r = radius inj = injector s = slot height t = total x = distance from film applicator throat = regarding nozzle throat

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“…ATLLAS, coordinated by ESA-ESTEC, is supported by the EU within the 6th Framework Programme Priority 1. 4 …”

Section: Acknowledgmentsmentioning

confidence: 97%

Section: B Film Models In Open Literaturementioning

confidence: 98%

Assessment of Analytical Models for Film Cooling in a Hydrocarbon/GOX Rocket Combustion Chamber

Kirchberger¹,

Schlieben²,

Haidn³

2012

48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

Self Cite

View full text Add to dashboard Cite

show abstract

Experimental and Numerical Film Cooling Investigations in a GOX/ Kerosene Rocket Combustion Chamber

Cited by 1 publication

References 4 publications

Assessment of Analytical Models for Film Cooling in a Hydrocarbon/GOX Rocket Combustion Chamber

Assessment of Analytical Models for Film Cooling in a Hydrocarbon/GOX Rocket Combustion Chamber

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