Turbine motor and blade interface cooling system

Fluid reaction surfaces (i.e. – impellers) – With heating – cooling or thermal insulation means – Changing state mass within or fluid flow through working...

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416219R, F01D 530

Patent

active

055119450

ABSTRACT:
Cooling air delivery systems for gas turbine engines are used to increase component life and increase power and efficiencies. The present system increases the component life and increases efficiencies by better utilizing the cooling air bled from the compressor section of the gas turbine engine. For example, a flow of cooling air which is directed through internal passages of the engine and into a cavity and is used to cool the interface between a turbine disc and a plurality of turbine blades and further reduces ingestion of hot power gases into the internal portion of the gas turbine engine. The cavity has a generally tapered configuration and effectively cools the interface between the disc and the blade. Thus, increasing component life and increasing power and efficiencies of the engine.

REFERENCES:
patent: 4582467 (1986-04-01), Kisling
patent: 5403156 (1995-04-01), Arness et al.

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