A High Resolution Turbine Cooling Prediction Method for Performance and Mechanical Integrity Calculations

Asterris Apostolidis, Panagiotis Laskaridis, Pericles Pilidis

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Abstract

Turbine blade cooling has been a topic of significant interest, as increasing turbine entry temperatures result in higher cooling requirements. The present numerical method divides the blade into a finite number of elements in the span and peripheral directions and solves the heat transfer fundamental equations for convection and conduction in both directions. As inputs, the span and chord gas temperature and heat transfer coefficient distributions are required. The results include high resolution temperature prediction for the blade and coolant, at all span and chord positions. The advantages of the method include the capturing of blade temperature variation in all directions, while considering the thermal diffusion due to conduction. Mach number effects to the resulted blade and coolant temperature are highlighted, as local distribution of the gas static temperature can have a dominant role. The effect of averaging the input parameters to the predicted blade temperature is discussed and finally, different values for the material conductivity are simulated and the results are analysed.
Original languageEnglish
Title of host publicationXXI International Symposium on Air Breathing Engines (ISABE 2013)
Subtitle of host publicationChallenges in Technology Innovation: Global Collaboration
Place of PublicationBusan
PublisherAmerican Institute for Aeronautics and Astronautics (AIAA)
Pages1-10
Volume1
ISBN (Print)9781629932866
Publication statusPublished - 9 Sep 2013
EventXXI International Symposium on Air Breathing Engines: Challenges in Technology Innovation: Global Collaboration - Busan, Korea, Republic of
Duration: 9 Sep 201313 Sep 2013

Conference

ConferenceXXI International Symposium on Air Breathing Engines
Abbreviated titleISABE 2013
Country/TerritoryKorea, Republic of
CityBusan
Period9/09/1313/09/13

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