Development of advanced technologies for future cryogenic thrust chamber applications

Zinner, W.; Haeseler, D.; Maeding, C.; Rubinskij, V.; Gorochov, V.; Hrisanfov, S.; Nikulin, G.

doi:10.2514/6.1997-3312

Cited by 5 publications

(4 citation statements)

References 1 publication

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“…Within TEKAN a continuation of the throttleable injector work [3] is forseen with hot firing on the P8 Test Facility.…”

Section: Throttleable Injector Headmentioning

confidence: 99%

“…Within the frame of the technology programme with CADB [3] injector elements for a throttling range of 25 % -100 % were investigated. The investigation was limited to coaxial injection elements, because the European ItyC^-trirust chambers use this type.…”

Section: Throttleable Injector Headmentioning

confidence: 99%

“…[1], [3], [4], [6]. Within the frame of different national technology programmes and in collaboration with the Technical University of Dresden [6] a systematic review and improvement of the existing prediction methods for the hot gas and the coolant side heat transfer was performed.…”

Section: Heat Transfer Analysismentioning

confidence: 99%

“…Compared to these conventional applications the extremely high heat flux in an ACE type combustion chamber in the order of up to 170 MW/m and the use of cryogenic hydrogen as coolant require new technology developments.Within the frame of the joint Dasa/CADB technology programme[3] a transpiration cooled modular subscale combustion chamber(Figure 7.5) will be hot fire tested by CADB in Voronezh. This chamber consists of hydrogen transpiration cooled and regeneratively water cooled sections.…”

mentioning

confidence: 99%

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Cryogenic liquid rocket engine technology developments within the German National Technology Programme

Immich

Mayer²

1997

33rd Joint Propulsion Conference and Exhibit

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In a joint technology programme Daimler-Benz Aerospace (Dasa) and the German Aerospace Research Establishment (DLR) are presently investigating technologies for advanced thrust chambers of reusable, high performance cryogenic rocket engines. This Technology Programme on Cryogenic Rocket Propulsion (TEKAN) has been established in 1996 under sponsorship of the German Space Agency DARA. In this programme the extensive experience of Dasa with regeneratively cooled liquid rocket engine combustion chambers is combined with the research oriented activities of DLR in liquid rocket propulsion in order to reach the targets.The present paper describes and discusses the technology developments within TEKAN which have been initiated.Rocket engine cycle analyses for different reusable launch vehicle concepts are performed in order to define the requirements for the thrust chamber components of future launch vehicle propulsion systems. In addition, a simulation tool is developed for transient engine analysis. Basic theoretical and experimental work on combustion chamber heat transfer, cooling, lifetime, and combustion modelling is continued in this programme. Technology developments of the main thrust chamber components as injectors and combustion chamber technologies for high lifetime (thermal barrier coatings, elastic liner technologies) are investigated with experimental test programmes on subscale level and theoretical analyses. Technologies for expander cycle engines are developed and the applicability of carbon fibre reinforced composite materials in cryogenic thrust chambers is investigated.

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“…Within TEKAN a continuation of the throttleable injector work [3] is forseen with hot firing on the P8 Test Facility.…”

Section: Throttleable Injector Headmentioning

confidence: 99%

Section: Throttleable Injector Headmentioning

confidence: 99%