Investigation of Sub- and Supercritical LOX/Methane Injection Using Optical Diagnostics

Lux, Johannes; Suslov, Dmitry; Bechle, M.; Oschwald, Michael; Haidn, Oskar

doi:10.2514/6.2006-5077

Cited by 10 publications

(4 citation statements)

References 20 publications

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“…All investigations presented in this paper were performed at the European Research and Technology Test Facility P8 at DLR Lampoldshausen using the subscale combustion chamber "B" 12,15) .…”

Section: Methodsmentioning

confidence: 99%

Experimental Investigation of Film Cooling with Tangential Slot Injection in a LOX/CH4 Subscale Rocket Combustion Chamber

Arnold¹,

Suslov²,

Haidn³

2009

Trans. JSASS Space Tech. Japan

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Within the frame of a broader activity towards research into the application of methane in cryogenic liquid rocket engines, the efficiency of film cooling was studied in a LOX/CH 4 fired subscale sized model combustor. Aiming at booster as well as upper stage applications, the combustion pressure levels have been varied between 4 MPa and 7 MPa. The effectiveness of the ambient temperature film was determined in axial and circumferential directions by measuring temperature gradients in the copper liner material. The experiments revealed remarkable circumferential differences of the film cooling efficiency which remain existent far downstream. However, circumferential film cooling varieties are more pronounced at close proximity of the point of film coolant injection.

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“…All investigations presented in this paper were performed at the European Research and Technology Test Facility P8 at DLR Lampoldshausen using the subscale combustion chamber "B" 12,15) .…”

Section: Methodsmentioning

confidence: 99%

Experimental Investigation of Film Cooling with Tangential Slot Injection in a LOX/CH4 Subscale Rocket Combustion Chamber

Arnold¹,

Suslov²,

Haidn³

2009

Trans. JSASS Space Tech. Japan

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“…Combustion stability 17 • With a single coax injector some low frequency instability (LF) was encountered when using CH4-film for cooling of windows for optical access. LF with CH4-film for window cooling (vary mixture ratio for total mass flow).…”

Section: Research Conductedmentioning

confidence: 99%

International Space Exploration Coordination Group Assessment of Technology Gaps for LOx/Methane Propulsion Systems for the Global Exploration Roadmap

et al. 2016

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As part of the Global Exploration Roadmap (GER), the International Space ExplorationCoordination Group (ISECG) formed two technology gap assessment teams to evaluate topic discipline areas that had not been worked at an international level to date. The participating agencies were ASI, CNES, DLR, ESA, JAXA, and NASA. Accordingly, the ISECG Technology Working Group (TWG) recommended two discipline areas based on Critical Technology Needs reflected within the GER Technology Development Map (GTDM): Dust Mitigation and LOX/Methane Propulsion. LOx/Methane propulsion systems are enabling for future human missions Mars by significantly reducing the landed mass of the Mars ascent stage through the use of in-situ propellant production, for improving common fluids for life support, power and propulsion thus allowing for diverse redundancy, for eliminating the corrosive and toxic propellants thereby improving surface operations and reusability, and for increasing the performance of propulsion systems. The goals and objectives of the international team are to determine the gaps in technology that must be closed for LOx/Methane to be used in human exploration missions in cis-lunar, lunar, and Mars mission applications. An emphasis is placed on near term lunar lander applications with extensibility to Mars. Each agency provided a status of the substantial amount of Lox/Methane propulsion system development to date and their inputs on the gaps in the technology that are remaining. The gaps, which are now opportunities for collaboration, are then discussed.

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“…So we designed several injector elements by referring other research results 1), 2) and selected better elements which have stable characteristics in cold flow and firing tests. Tests flow is shown in Fig.…”

Section: Development Risks and Mitigation Tests Planmentioning

confidence: 99%

Combustion and Regenerative Cooling Characteristics of LOX/Methane Engine

Kawashima

Okita

Aoki

et al. 2009

Trans. JSASS Space Tech. Japan

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The regenerative cooled LOX/methane engine is considered by the cooperative research with JAXA, MHI, and IHI. As a part of this cooperation, the experiments and analysis about LOX/methane combustion instability and regenerative cooling characteristics were carried out because the lack of the fundamental LOX/methane properties was identified as a risk through engine design, production, test, and operation.

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Investigation of Sub- and Supercritical LOX/Methane Injection Using Optical Diagnostics

Cited by 10 publications

References 20 publications

Experimental Investigation of Film Cooling with Tangential Slot Injection in a LOX/CH4 Subscale Rocket Combustion Chamber

Experimental Investigation of Film Cooling with Tangential Slot Injection in a LOX/CH4 Subscale Rocket Combustion Chamber

International Space Exploration Coordination Group Assessment of Technology Gaps for LOx/Methane Propulsion Systems for the Global Exploration Roadmap

Combustion and Regenerative Cooling Characteristics of LOX/Methane Engine

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