Turbine blade cooling system

Details Turbine blade cooling system Turbine blade cooling system

2005-10-19

2008-12-02

Kershteyn, Igor (Department: 3745)

Rotary kinetic fluid motors or pumps

Method of operation

C415S115000, C415S175000, C415S116000, C416S09700R

Reexamination Certificate

active

07458766

ABSTRACT:
Efficient cooling of a stage of gas turbine engine turbine blades (36) is achieved by first reducing the pressure of the cooling air after it has been bled from the annulus of the compressor (12) by passing it through a diffuser (30), to a pressure magnitude lower than is required at entry to the turbine blades, then re-pressurizing the bled air up to the required entry pressure, by passing it through a radial compressor defined by a cowl (44) positioned in close spaced, co-rotational relationship with the downstream face of the associated turbine disk (34).

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