Fluid-thermo-structural response of actively cooled scramjet combustor in hypersonic accelerating-cruise flight

Gopinath, NK and Govindarajan, KV and Mahapatra, DR (2022) Fluid-thermo-structural response of actively cooled scramjet combustor in hypersonic accelerating-cruise flight. In: International Journal of Heat and Mass Transfer, 194 .

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Abstract

This paper presents a three-dimensional transient fluid-thermo-structural study of an actively cooled sandwich panel under hypersonic accelerating-cruise flight conditions. The thermo-structural loads are estimated using a high-speed gas-dynamic flow model combined with Eckert's reference temperature method. The thermal safeguard capacity with endothermic fuel-based active cooling shows design optimization scope compared to the passive system. A passive system has to survive excessively high temperatures with a less severe thermal gradient over the panel thickness and a high heat leakage into the structural interior or back wall. The actively cooled system with fuel develops significant panel bending due to a through-thickness thermal gradient in the cooling channels. For a Mach 7 flight, an actively cooled system reduces the bending deformation by 90 and improves the thermal safeguard capacity by 70 compared to a passive approach. Active cooling can effectively control the excessive thermo-structural deformation and fuel heating below its cracking temperature to improve combustion. Our parametric design study indicates the influence of fuel as a coolant for increasing combustion efficiency and the associated complexity and trade-off in the heat transfer and thermo-structural deformation behavior. This transient response under hypersonic accelerating-cruise flight conditions requires a careful review of the scramjet engine thermo-structural design philosophy. The design approach has applications in bodies encountering highly transient thermo-structural loads with differently purposed fuels/coolants. © 2022

Item Type:	Journal Article
Publication:	International Journal of Heat and Mass Transfer
Publisher:	Elsevier Ltd
Additional Information:	The copyright for this article belongs to the Elsevier Ltd.
Keywords:	Heat transfer; Hydrocarbon fuel; Regenerative cooling; Sandwich panel; Thermo-structure
Department/Centre:	Division of Mechanical Sciences > Aerospace Engineering(Formerly Aeronautical Engineering)
Date Deposited:	15 Jun 2022 09:41
Last Modified:	15 Jun 2022 09:41
URI:	https://eprints.iisc.ac.in/id/eprint/73569

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