Effusion cooling in rocket combustors applying fibre reinforced ceramics

Serbest, Erhan; Haidn, Oskar; Hald, Hermann; Korger, G.; Winkelmann, Peter

doi:10.2514/6.1999-2911

Cited by 7 publications

(2 citation statements)

References 6 publications

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“…The properties of C/C, as small heat conductivities (1 − 1.2 W/mK), insensibility against thermal shocks and very high tolerable wall temperatures (≥ 2500 K) (see [11], [4], [12] and [13]), make C/C structures especially suited for components with very high thermal loads. Additionally, due to the avoidance of thermal shock problems C/C structures are also attractive in terms of re-usability and its comparatively low densities (1.3−1.4 g/cm 3 ) is especially interesting considering light weight design.…”

Section: Research and Development Strategymentioning

confidence: 99%

“…A typical example are the test firings of a small storable propellant thruster (400 N class) reported by Astrium [2]. Within the first to report hot-fire tests of actively cooled ceramic combustion chamber liners in the 6-10 MPa range were NASA Marshall Space Flight Center [3] and DLR Lampoldshausen [4]. * Copyright c 2003 by the International Astronautical Federation.…”

Section: Introductionmentioning

confidence: 97%

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CMC Rocket Combustion Chamber with Effusion Cooling

Hald¹,

Ortelt²,

Fischer³

et al. 2003

54th International Astronautical Congress of the International Astronautical Federation, the International Academy of Astronaut

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New propulsion systems play a key role for future space transportation systems (STS). While high efficiency with respect to specific impulse is mandatory aspects concerning system design (complexity, manufacturing, weight), operating aspects (reusability, maintenance, high reliability and safety) and cost reduction attract increasing attention. A significant step forward seems to be the application of high temperature usable ceramic matrix composites (CMC) within a cryogenic combustion chamber design. The approach is using a porous fibre ceramic inner combustion chamber liner. Operating temperatures of the CMC material lie far upper than 1800 • C. Nevertheless an appropriate cooling method has to be applied accompanied by temperatures of about 2700 • C running the combustion process. While the porous CMC is responsible for both thermal load absorption and the effusion cooling the mechanical load carrying structure consists on a carbon fibre reinforced plastic (CFRP) outer shell. Using both ring shaped ceramic combustion chamber segments on 1-10 MPa pressure levels and a complete ceramic thrust chamber design on 1 MPa pressure level samples demonstrated already the physical principles. The paper will give an overview of the current development status, whereby the experience achieved so far is very promising out looking to the general goals.

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Section: Research and Development Strategymentioning

confidence: 99%