Near wall compartment cooled turbine blade

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

Reexamination Certificate

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C416S09000A

Reexamination Certificate

active

08047790

ABSTRACT:
A turbine blade used in a gas turbine engine, the blade includes a plurality of cooled zones each with a plurality of radial extending cooling passages formed within the wall of the blade and connected to a separate collection cavity. A leading edge collection cavity is supplied with cooling air through a plurality of radial extending cooling channels located in the wall around the leading edge of the blade. Film cooling holes connected to the leading edge collection cavity discharge film cooling air to the leading edge. A pressure side collection cavity is supplied with cooling air from a plurality of pressure side radial extending cooling channels and discharges cooling air through film cooling holes on the pressure side. A suction side collection cavity is supplied with cooling air through a plurality of suction side radial cooling channels and discharges cooling air through suction side film cooling holes.

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patent: 2002/0197160 (2002-12-01), Liang

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