Ptah-socar fuel-cooled composite materials structure

Bouchez, Marc; Beyer, Steffen

doi:10.1051/eucass/200901627

Cited by 19 publications

(11 citation statements)

References 2 publications

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“…To evaluate the geometric effect of actual combustion chamber in addition to the material behavior of the CMC in the combustion atmosphere, micro combustion chambers are manufactured using the PTAH-SOCAR technology 6,8,10 . Using the ERBURIG K test facility of Airbus Group Innovations in Ottobrunn (Germany), the cooled CMC micro combustion chambers are tested for long duration (hours) instead of minutes 6 .…”

Section: Cooled Cmc Micro Combustion Chamber Long Duration Testingmentioning

confidence: 99%

Combustor Materials Research Studies for High Speed Aircraft in the European Program ATLLAS2

Bouchez¹,

Dufour²,

Naour³

et al. 2015

20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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Hypersonic airliner would be exposed to temperatures that are beyond the limits of classical aircraft materials. In order to handle this problem the latest developments of new materials and composite structures suitable for high temperature application need to be taken into account. The focus of the European Research program ATLLAS is on advanced light-weight, high-temperature material development strongly linked to a high-speed passenger aircraft design. ATLLAS stands for Aerodynamic and Thermal Load Interactions with Lightweight Advanced Materials for High Speed Flight. The 4.5 years program ATLLAS-II is a logical continuation project built upon the experience and technology development gained within ATLLAS-I. The corresponding work related to combustor structures and material integration deals with the opportunity to investigate at academic level, both in basic and relevant environment, different solutions possibly usable to ensure the long range cruise of a high speed airliner. Different materials (UHTC, CMC, metallic) and different cooling techniques (radiation, convective, transpiration) are studied. Available 2 numerical or semi-empirical tools are used to prepare the test, to design the different architectures. A pin fin experiment allows to better know the pressure drop and the heat transfer for different channel patterns with thermal crystal techniques. The ERBURIG K long duration test facility allows to characterize different ceramic matrix composite uncooled samples to realize, at small scale, a long duration (several hours) investigation of cooled ceramic structure in PTAH-SOCAR technology. A multifunctional metallic transpiration cooled HSS panel using Hollow Spheres Stacking as core material was designed and preliminary tested in cold conditions with GN2 and in hot conditions with infra-red lamps under 1 MW/m² heat flux before successful METHYLE testing in supersonic reacting flow. CMC and UHTC materials are used to design, manufacture and test generic fin injectors usable in high speed combustors. Industrial hypersonic METHYLE test facility is used to test in relevant Mach 6 combustor environment CMC and HSS panel as well as advanced fin injectors. Hot and cold permeability of composites is also documented with GN2 and GH2, taking into account the mechanical stress possible effect. Numerical models are used in accordance with the experiments, some examples are also given in the present paper. NomenclatureC/C-SiC = carbon fibre reinforced silicon carbide CFD = computational fluid dynamics CMC = ceramic matrix composite ERBURIG K = Environmental Relevant Burner Rig -Kerosene HSS = Hollow Spheres Stacking (sandwich) FEM = finite elements (mechanical computational) method GN 2 = gaseous nitrogen METHYLE= French acronym for long duration hypersonic technology test facility O 2 = oxygen SiC/SiCN = silicon carbide fibre reinforced silicon carbonitride TLC = Thermochromic Liquid Crystals UHTC = ultra high temperature ceramics

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Section: Cooled Cmc Micro Combustion Chamber Long Duration Testingmentioning

confidence: 99%

Combustor Materials Research Studies for High Speed Aircraft in the European Program ATLLAS2

Bouchez¹,

Dufour²,

Naour³

et al. 2015

20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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“…Additionally Astrium designed two PTAH-SOCAR combustion chamber segments which are manufactured of CARBOTEX® material [13]. After the inner diameter of the liner has been braided, a spacer foam was applied in order to form the coolant passage before the outer diameter of the liner was manufactured.…”

Section: Figure 12: Dlr Cologne Heat Flux Sensormentioning

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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“…Today, the development of the fuel-cooled C/SiC structure technology is pursued, not only for high-speed airbreathing application (Ref 21 ), and will lead to new demonstration step in 2009 by taking advantage of the new test facility METHYLE (Ref 22 ).…”

Section: Fig 1-cooled Composite Combustion Chamber Duct (In Red) Testmentioning

confidence: 99%

French Flight Testing Program LEA Status in 2009

Falempin

Serre²

2009

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

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French R&T effort for hypersonic airbreathing propulsion is focusing on needed technologies for the propulsion system and acquisition of aero-propulsive balance prediction capability. A large part of technology development effort can be led on ground and is currently dedicated to combustion chamber to ensure its performance and thermomechanical strength. On the contrary, it is mandatory to flight demonstrate capability to predict the aero-propulsive balance. In that view, MBDA and ONERA are leading the flight testing LEA program. Started in January 2003, the program will end in 2015 after 4 autonomous flight tests of an experimental vehicle in Mach number range 4 to 8. Guidelines for LEA vehicle and its propulsion system design have been validated in 2006 by a Preliminary Design Review. The running Phase 2 aims at getting a detailed design while validating the aero-propulsive configuration by a first free jet test series to be performed early in 2011.

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Ptah-socar fuel-cooled composite materials structure

Cited by 19 publications

References 2 publications

Combustor Materials Research Studies for High Speed Aircraft in the European Program ATLLAS2

Combustor Materials Research Studies for High Speed Aircraft in the European Program ATLLAS2

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

French Flight Testing Program LEA Status in 2009

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