Heat Transfer Augmentation in Gas Turbine Blade Passages

Penulis
Tiada maklumat
Penerbit
LAP Lambert Academic Publishing
Diterbitkan
20190513
ISBN
9786200078636
Kawasan pendaftaran ISBN
Mauritius (ISBN 978-620)

Huraian

In general, gas turbine cooling is achieved by bleeding some relatively cool air from the compressor and using it inside the gas turbine blades to remove heat transferred into the blade from the hot mainstream. The cooling air flows through internal cooling passages inside the blade. These passages are specifically designed to maximize the heat transfer.