Abstract
The overall efficiency of gas turbines used in aeronautical systems and ground-based power generation can be significantly improved using a higher turbine inlet temperature and a higher compressor pressure ratio. Elevating the turbine inlet temperature results in a much higher heat transfer rates via forced convection from hot gasses to turbine components. The three categories of turbomachinery heat transfer research discussed are: computational methods; impingement cooling; and film cooling.
Original language | English (US) |
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Pages (from-to) | 347-348 |
Number of pages | 2 |
Journal | American Society of Mechanical Engineers, Heat Transfer Division, (Publication) HTD |
Volume | 361-3 |
State | Published - Dec 1 1998 |
Event | Proceedings of the 1998 ASME International Mechanical Engineering Congress and Exposition - Anaheim, CA, USA Duration: Nov 15 1998 → Nov 20 1998 |
All Science Journal Classification (ASJC) codes
- Mechanical Engineering
- Fluid Flow and Transfer Processes