Testing of Refractory Composites for Scramjet Combustors

Glass, David E.; Capriotti, D. P.; Reimer, Thomas; Kütemeyer, Marius; Smart, Michael K.

doi:10.2514/1.b36147

Cited by 8 publications

(5 citation statements)

References 9 publications

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“…Moreover, the Langley Research Center of NASA also conducted a series of tests on CMC heat-resistant materials used in propulsion systems [35], and the experimental test equipment is shown in Figure 4. In this experiment, transient one-dimensional thermal analysis was carried out by installing thermocouples, and the maximum wall surface temperature calculated reached about 1400 • C. It was also pointed out that C/C-SiC and C/C can be used as burner materials for passive scramjets during short-term test flights.…”

Section: Latest Research Progress Of Passive Thermal Protectionmentioning

confidence: 99%

Thermal Protection System and Thermal Management for Combined-Cycle Engine: Review and Prospects

et al. 2019

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Combined-cycle engine is a potential propulsion system for hypersonic aircraft. To ensure long-term, normal operation of combined-cycle engine under the harsh environment of high thermal load, it is of great significance to study the thermal protection and management of the propulsion system. In this study, the objective and development status of thermal protection and thermal management systems for the combined-cycle propulsion system were described. The latest research progresses of thermal protection, thermal barrier coating, and thermal management system of the combined-cycle propulsion system were summarized. Moreover, the problems and shortcoming in current researches were summarized. In addition, a prospect for the future development of thermal protection and management of the combined-cycle propulsion system was presented, pointing out a direction of great value and vital research significance to thermal protection and management of the combined-cycle propulsion system.

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Section: Latest Research Progress Of Passive Thermal Protectionmentioning

confidence: 99%

Thermal Protection System and Thermal Management for Combined-Cycle Engine: Review and Prospects

et al. 2019

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Section: Introductionmentioning

confidence: 99%

“…Development of materials capable of retaining their mechanical properties at temperatures~1800°C is the most important step in the realization of hot structures of hypersonic space vehicles. 1,2 Carbon fiber reinforced ceramic matrix composites (CMCs) are prime candidates for such applications because of high strength, hardness, chemical inertness, low density, and high service temperatures. [3][4][5] Recently ceramic composites have also being evaluated for their multifunctional properties such as electromagnetic shielding, self-healing, and self-lubrication characteristics.…”

Section: Introductionmentioning

confidence: 99%

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A comparative study on C_f/PyC/SiC minicomposites prepared via CVI process for hypersonic engine application

Krishnan

Vijay

Siva

et al. 2018

Int J Applied Ceramic Tech

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Carbon fiber reinforced silicon carbide (SiC) minicomposites were prepared from three variants of commercially available carbon fibers, viz., T300‐3K, T300J‐3K, and T300‐6K. The SiC matrix infiltration was done via chemical vapor infiltration process using methyltrichlorosilane as the precursor. Minicomposites were characterized for the composition and morphology of the matrix material deposited. It was found that the matrix contains 2H‐SiC along with the major phase 3C‐SiC. Cyclic tensile tests were carried out on the composites to understand the damage mechanism and load bearing characteristics under cyclic loading conditions. The dependence of peak and residual strains on the fiber volume fraction was studied. Oxidation of the CMCs in air at 1500°C was studied and the result was explained based on a five part process.

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“…Its ability to perform under high thermal stress environments has also been tested, namely for uses within scramjet combustors. These tests showed the plate material reaching a total of 1400 0 C after 120 seconds at Mach 5 conditions (Glass , Smart, & Capriotti, 2016).…”

Section: Main Bodymentioning

confidence: 96%

UQ eSpace

Stephens¹

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Vehicles travelling at Mach 5 and greater are subject to intense thermal loadings, with the vehicle's ability to withstand this being a major design consideration. When determining thermal protection systems, one has the option of passively or actively cooling the surface. For this investigation, passive cooling techniques have been analysed with a series of geometric test cases (comprising 3 key geometric parameters), in order to determine the temperatures and thermal gradients achieved by SPARTAN's nose cone. SPARTAN is the second stage in a proposed three stage access to space vehicle and will utilise a scramjet engine, improving efficiency and cost. By computing convection coefficients and flow temperatures using aerothermodynamic theory, the boundary conditions can be quickly updated and imported to ANSYS for the transient thermal analysis. This investigation found that a 5mm tip radius, 50mm tip length and 5mm body thickness is sufficient for protecting SPARTAN from the harsh environment, reaching temperatures in the order or 3000 o K at the tip and 1400 o K on the CMC body.

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Testing of Refractory Composites for Scramjet Combustors

Cited by 8 publications

References 9 publications

Thermal Protection System and Thermal Management for Combined-Cycle Engine: Review and Prospects

Thermal Protection System and Thermal Management for Combined-Cycle Engine: Review and Prospects

A comparative study on C_f/PyC/SiC minicomposites prepared via CVI process for hypersonic engine application

UQ eSpace

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Testing of Refractory Composites for Scramjet Combustors

Cited by 8 publications

References 9 publications

Thermal Protection System and Thermal Management for Combined-Cycle Engine: Review and Prospects

Thermal Protection System and Thermal Management for Combined-Cycle Engine: Review and Prospects

A comparative study on Cf/PyC/SiC minicomposites prepared via CVI process for hypersonic engine application

UQ eSpace

Contact Info

Product

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About

A comparative study on C_f/PyC/SiC minicomposites prepared via CVI process for hypersonic engine application