Selection of a turbine cooling system applying multi-disciplinary design considerations.
The presented paper describes a multi-disciplinary cooling selection approach applied to major gas turbine engine hot section components, including turbine nozzles, blades, discs, combustors and support structures, which maintain blade tip clearances. The paper demonstrates benefits of close interaction between participating disciplines starting from early phases of the hot section development. The approach targets advancements in engine performance and cost by optimizing the design process, often requiring compromises within individual disciplines.
Glezer
B
B
Optimized Turbine Solutions, San Diego, California 92130, USA.