Film cooling analysis of injection configurations for afterburner aero-engine applications.

dc.contributor.author	Singh, Ashutosh Kumar
dc.date.accessioned	2023-12-18T06:36:05Z
dc.date.available	2023-12-18T06:36:05Z
dc.date.issued	2023
dc.description	Supervisors: Sahoo, Niranjan and Singh, Dushyant
dc.description.abstract	There is a significant need for thrust augmentation in aircraft for several specific operations, such as combat or take-off from short runways. The additional thrust requirement is achieved by burning extra fuel in the afterburner, which further raises the temperature to 2200K. In order to increase thermal efficiency and power output, the turbine entry temperature of modern gas turbine engines has to be increased considerably. Furthermore, the exposed components in the pathway of the exhaust stream experience a very high temperature. Therefore, to maintain the permissible metal temperature for safe operation, the component under such high thermal loads requires a sophisticated cooling technique. “Film cooling” is one of the most adopted to protect the component which is subjected to hot flue gases.	en_US
dc.identifier.other	ROLL NO.186103109
dc.identifier.uri	https://gyan.iitg.ac.in/handle/123456789/32
dc.language.iso	en	en_US
dc.relation.ispartofseries	TH-3231;
dc.subject	Department of Mechanical Engineering	en_US
dc.subject	MECHANICAL ENGINEERING
dc.title	Film cooling analysis of injection configurations for afterburner aero-engine applications.
dc.type	Thesis

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