Hot-firing of an advanced 40 kN thrust chamber

Alting, J.; Grauer, Frank; Hagemann, G.; Kretschmer, J.

doi:10.2514/6.2001-3260

Cited by 11 publications

(5 citation statements)

References 2 publications

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“…Aerospace industry is carrying out research in the space propulsion section technology with different material concepts, trying to achieve low cost and preparation materials for their applications [26]. For propulsion systems, a great challenge is the implementation of a high thrust to mass ratio [27]. Ceramic fiber composites have been used in radiationcooled nozzle extensions as well as combustion chambers for small thrusters.…”

Section: Potential Use Of O-cmcs In Aeroenginesmentioning

confidence: 99%

Oxide Ceramic Matrix Composite Materials for Aero-Engine Applications: A Literature Review

Karadimas¹,

Salonitis²,

Georgarakis³

2021

Advances in Transdisciplinary Engineering

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The development of aircraft gas turbine engines has extensively been required for the development of advanced materials. This complex development process is however justified by the system-level benefits in terms of reduced weight, higher temperature capability, and/or reduced cooling, each of which increases efficiency. This is where high-temperature ceramics have made considerable progress and ceramic matrix composites (CMCs) are in the foreground. CMCs are classified into non-oxide and oxide-based ones. Both families have material types that have a high potential for use in high-temperature propulsion applications. Typical oxide-based ones are based on an oxide fiber and oxide matrix (Ox-Ox). Some of the most common oxide subcategories, are alumina, beryllia, ceria, and zirconia ceramics. Such matrix composites are used for example in combustion liners of gas turbine engines and exhaust nozzles. However, until now a thorough study on the available oxide-based CMCs for such applications has not been presented. This paper focus on assessing a literature survey of the available oxide ceramic matrix composite materials in terms of mechanical and thermal properties.

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Section: Potential Use Of O-cmcs In Aeroenginesmentioning

confidence: 99%

Oxide Ceramic Matrix Composite Materials for Aero-Engine Applications: A Literature Review

Karadimas¹,

Salonitis²,

Georgarakis³

2021

Advances in Transdisciplinary Engineering

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“…14 ' 15 The high quality of the test results allow their use for computational fluid dynamics (CFD) validation purposes. 14 ' 15 The high quality of the test results allow their use for computational fluid dynamics (CFD) validation purposes.…”

Section: Supersonic Nozzle Wall Heat Transfer For High-temperaturementioning

confidence: 99%

Simulation and Analysis of Thrust Chamber Flowfields: Cryogenic Propellant Rockets

Preclik¹,

Knab²,

Görgen³

et al. 2004

Liquid Rocket Thrust Chambers

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“…An interesting representative of the group of CMCs comprises carbon fiber‐reinforced silicon carbide‐C/SiC, which is made using the LPI process (liquid polymer infiltration). Figure 1 illustrates the excellent ratio of strength to weight, in particular at high temperatures, compared with currently utilized metal materials, which is just one special feature that makes it attractive as a construction material 1,2 . In the sector of space propulsion systems, to date, ceramic fiber composites have been used primarily for radiation‐cooled nozzle extensions and combustion chambers for small thrusters; the advantage here lies in the low specific weight (lightweight construction), dispensing with active cooling and at the same time high service temperatures.…”

Section: Introductionmentioning

confidence: 99%

“…Due to the above advantages inherent in ceramic fiber composites, currently engine manufacturers and research institutes are stepping up their activities geared toward the use of ceramics in rocket‐engine thrust‐chamber components. In view of the extreme thermomechanical loads in the combustion chamber of liquid‐propellant rocket engines, previous developments concentrated above all on the use of ceramic fiber composites in the less thermally loaded nozzle extensions 1 . At EADS‐ST, nozzle extensions have been developed to date made of C/SiC for the upper‐stage engine AESTUS and successfully tested on the altitude test bench P4.1 at DLR in Lampoldshausen.…”

Section: Introductionmentioning

confidence: 99%

“…In view of the extreme thermomechanical loads in the combustion chamber of liquidpropellant rocket engines, previous developments concentrated above all on the use of ceramic fiber composites in the less thermally loaded nozzle extensions. 1 At EADS-ST, nozzle extensions have been developed to date made of C/SiC for the upper-stage engine AES-TUS and successfully tested on the altitude test bench P4.1 at DLR in Lampoldshausen. A subscale nozzle on the scale of 1:5 for the Ariane 5 main engine Vulcain was made of C/SiC and also successfully tested on the research test bench P8 at DLR in Lampoldshausen at combustion-chamber pressures of up to 80 bar.…”

Section: Introductionmentioning

confidence: 99%

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Ceramic Matrix Composites: A Challenge in Space‐Propulsion Technology Applications

Schmidt

Beyer

Immich

et al. 2005

Int J Applied Ceramic Tech

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Various technology programs in Europe are concerned, besides developing reliable and rugged, low‐cost, throwaway equipment, with preparing for future reusable propulsion technologies. One of the key roles for realizing reusable engine components is the use of modern and innovative materials. One of the key technologies that concerns various engine manufacturers worldwide is the development of fiber‐reinforced ceramics—CMCs (ceramic matrix composites). The advantages for the developers are obvious–the low specific weight, the high specific strength over a large temperature range, and their great damage tolerance compared with monolithic ceramics make this material class extremely interesting as a construction material. Over the past few years, the EADS‐ST Company (formerly DASA) has, together with various partners, worked intensively on developing components for hypersonic engines and liquid rocket propulsion systems. In the year 2000, various hot‐firing tests with subscale (scale 1:5) and full‐scale nozzle extensions were conducted. In this year, a further decisive milestone was achieved in the sector of small thrusters, and long‐term tests served to demonstrate the extraordinary stability of the C/SiC material. Besides developing and testing radiation‐cooled nozzle components and small‐thruster combustion chambers, EADS‐ST worked on the preliminary development of actively cooled structures for future reusable propulsion systems. In order to get one step nearer to this objective, the development of a new fiber composite was commenced within the framework of a regionally sponsored program. The objective here is to create multidirectional (3D) textile structures combined with a cost‐effective infiltration process. Besides material and process development, the project also encompasses the development of special metal/ceramic and ceramic/ceramic joining techniques as well as studying and verifying nondestructive investigation processes for the purpose of testing components.

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Hot-firing of an advanced 40 kN thrust chamber

Cited by 11 publications

References 2 publications

Oxide Ceramic Matrix Composite Materials for Aero-Engine Applications: A Literature Review

Oxide Ceramic Matrix Composite Materials for Aero-Engine Applications: A Literature Review

Simulation and Analysis of Thrust Chamber Flowfields: Cryogenic Propellant Rockets

Ceramic Matrix Composites: A Challenge in Space‐Propulsion Technology Applications

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