978-620-0-07863-6

Heat Transfer Augmentation in Gas Turbine Blade Passages

Mohammed W. Al-Jibory

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Summary:

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. In modern gas turbine blades, this is usually done by the use of contact area enhancers and turbulence promoters, such as ribs and pin-fins in the passages. Some of this cooling air is ejected onto the surface of the turbine blade to form an insulating film - with the goal of reducing contact of the blade with the hot mainstream gas.

Author:

Hasan Qahtan

Biographie:

Hassan Qahtan Hussein Ali Eid was born on November, 17th 1989 in Dhi Qar-Souk al-Shuyukh. He is living in Karbala, Iraq. He is married.

Author:

Farhan Lafta

Biographie:

Number of Pages:

124

Book language:

English

Published On:

2019-05-13

ISBN:

978-620-0-07863-6

Publishing House:

LAP LAMBERT Academic Publishing

Keywords:

gas turbine, Nanomaterial

Product category:

TECHNOLOGY / Engineering / General