Cooling structure for a gas turbine
AssigneeMitsubishi Heavy Industries, Ltd.
InventorsShunsuke Torii, Jun Kubota, Yasuoki Tomita, Hiroyuki Aoki, Masamitsu Kuwabara
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Abstract
In a cooling structure for a gas turbine, cooling air diffusion holes are formed from inner surface to outer surface of a platform so as to open from high pressure side blade surface of a moving blade offset in a direction toward low pressure side blade surface of adjacent moving blade confronting the high pressure side blade surface, in a direction of primary flow.
Claims9
A cooling structure for a gas turbine having high temperature members that include a platform of a turbine moving blade, a shroud of a turbine stationary blade, and a turbine blade, and having multiple diffusion holes formed on the high temperature members for film cooling thereof by blowing cooling medium to outer surface of the high temperature members,
- wherein the platform of the turbine moving blade has first diffusion holes which are formed on a first outer surface of the platform facing a high pressure side of the turbine moving blade and second diffusion holes on a second outer surface of the platform facing a low pressure side of the turbine moving blade so that each hole of the first diffusion holes blows the cooling medium in a direction separating from the high pressure side of the turbine moving blade and each hole of the second diffusion holes blows the cooling medium in a direction heading towards the low pressure side of the turbine moving blade.
Dependencies are inferred from the claim text.