Investigation on Film Cooling in a Kerosene/GOX Combustion Chamber

Kirchberger, Christoph; Schlieben, Gregor; Hupfer, Andreas; Kau, Hans-Peter; Martin, Philip; Soller, Sebastian

doi:10.2514/6.2009-5406

Cited by 16 publications

(4 citation statements)

References 5 publications

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“…The hot wall heat transfer coefficient is, for the case used, calculated from a modified formulation proposed by Sinyarev. 14) General information about Thermtest can be found in Kirchberger et al 15) In the past, Thermtest has been validated and adapted for the use of kerosene/oxygen as propellants in small single-element combustion chambers featuring swirl or double swirl coaxial injector elements 16) and for a single element capacitive combustion chamber using methane/oxygen. 17) Efforts have been done to further validate the tool for methane/oxygen propellant combination and to adapt the empirical correlations to the injector behavior.…”

Section: (4)mentioning

confidence: 99%

Experimental and Numerical Investigation of a Multi-Injector GOX-GCH4 Combustion Chamber

Silvestri

Kirchberger

Schlieben

et al. 2018

AEROSPACE TECHNOLOGY JAPAN

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In the current study results from an experimental investigation on an oxygen/methane multi-injector combustion chamber are presented. They provide detailed information about the thermal loads at the hot inner walls of the combustion chamber at representative rocket engine conditions and pressure ranges up to 40 bar. The present study aims to contribute to the understanding of the thermal transfer processes and of the interaction between the injectors and the injector-wall. Furthermore, the test results are used as a test case for the validation of the in-house engineering tool Thermtest. Due to the complex flow phenomena linked to the use of cryogenic propellants, like extreme variation of flow properties and steep temperature gradients, in combination with intensive chemical reactions, the problem has been partially simplified by injecting the propellants in gaseous form.

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Section: (4)mentioning

confidence: 99%

Experimental and Numerical Investigation of a Multi-Injector GOX-GCH4 Combustion Chamber

Silvestri

Kirchberger

Schlieben

et al. 2018

AEROSPACE TECHNOLOGY JAPAN

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“…The design of the film cooling experiment is finalized and the first part of the experiments is finalized [12] below. The operating points are chosen in order to allow for a comparison of the different cooling techniques.…”

Section: Increased Engine Thermal Efficiency: Novel Cooling Conceptsmentioning

confidence: 99%

Achievements obtained on Aero-Thermal Loaded Materials for High-Speed Atmospheric Vehicles within ATLLAS

Steelant¹

2009

16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference

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The project ATLLAS (Aerodynamic and Thermal Load Interactions with Lightweight Advanced Materials for High Speed Flight) kicked off in October 2006. Its main objective is to evaluate and assess potential high-temperature resistant materials for sustained superand hypersonic flight. This covers both materials for the external geometry as well as for the internal combustor geometries. The project, led by ESA-ESTEC, is co-funded by the European Commission under the 6 th Framework Program and a consortium of 13 partners from industry, research institutions and universities.The objective is to identify and assess lightweight advanced materials which can withstand ultra high temperatures and heat fluxes enabling high-speed flight above Mach 3. At these high speeds, classical materials used for airframes and propulsion units are not longer feasible and need to be replaced preferably by high-temperature, lightweight materials and if required, some parts with active cooling. Both metallic and non-metallic materials are tested extensively including Ni-based Hollow Sphere Packings, Ultra High Temperature Composites and several (non)-oxide Ceramic Matrix Composites. Envisaged cooling techniques for CMC based combustion liners are film, effusion, transpiration and regenerative cooling.

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“…The peak heat flux recorded without film cooling was about 65 Btu/in 2 -s, whereas the peak heat flux was about 48 Btu/in 2 -s with 16.4 inches upstream film injector and 20 Btu/in 2 -s with the 4.4 inches upstream injector. Kirchberger 2 conducted film cooling experiments on a 1500 psi bench-scale heat-sink test article American Institute of Aeronautics and Astronautics DISTRIBUTION A: Approved for public release; distribution unlimited running on GOX and kerosene. His results showed that kerosene is a much more effective film coolant than nitrogen.…”

Section: Introductionmentioning

confidence: 99%

“…Graduate Student, School of Aeronautics and Astronautics, Member AIAA 2. Mechanical Engineer, RZSA, Member AIAA.…”

mentioning

confidence: 99%

Studies in Optimizing the Film Flow Rate for Liquid Fuel Film Cooling

Miller¹,

Coy²

2011

47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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Investigation on Film Cooling in a Kerosene/GOX Combustion Chamber

Cited by 16 publications

References 5 publications

Experimental and Numerical Investigation of a Multi-Injector GOX-GCH4 Combustion Chamber

Experimental and Numerical Investigation of a Multi-Injector GOX-GCH4 Combustion Chamber

Achievements obtained on Aero-Thermal Loaded Materials for High-Speed Atmospheric Vehicles within ATLLAS

Studies in Optimizing the Film Flow Rate for Liquid Fuel Film Cooling

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