For aircraft propulsion, land based power generation, and other industrial applications such as trains, marines, automobiles, etc., gas turbines are commonly used. The operating temperature must be raised to increase the thermal performance and output work of the gas turbine engine to accommodate the accelerated production of modern gas turbines. The heat transmitted to the turbine blade, however is greatly increased as the temperature of the turbine inlet is constantly increased. For a long service life and healthy running, it is also very important to cool the turbine blades. Currently available methods for cooling turbine blades include film cooling with impingement cooling for the front edge, turbulent rib cooling with serpentine passages for the middle section of the blade, and pin fin cooling for the trailing edge of the turbine blade. The cooling system for turbine blades must provide cooling for all potential regions that are subjected to hot gas flow. This paper provides a literature review of blade tip leakage and heat transfer, as well as studies into external and internal cooling technologies.
by Prof. Amol Kumar Tripathi | Neha Verma "A Review Paper on Gas Turbine Blade Cooling Methods"
Published in International Journal of Trend in Scientific Research and Development (ijtsrd), ISSN: 2456-6470, Volume-5 | Issue-1 , December 2020,
URL: https://www.ijtsrd.com/papers/ijtsrd37999.pdf
internationaljournalofscience, openaccessjournalofscience, ugcapprovedjournalsforscience
No comments:
Post a Comment