Gas turbine engine aerofoil

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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Details

C415S172100

Reexamination Certificate

active

06837683

ABSTRACT:
A gas turbine engine blade or vane comprises inner linked chambers. A chamber adjacent the leading edge is provided with an inlet for receiving cooling fluid and a chamber adjacent the trailing edge is provided with an outlet for exhausting cooling fluid. The chambers are arranged in series from the leading edge to the trailing edge so as to direct cooling fluid within the aerofoil blade or vane from the leading edge region to the trailing edge region.

REFERENCES:
patent: 3732031 (1973-05-01), Bowling et al.
patent: 5246340 (1993-09-01), Winstanley
patent: 5667359 (1997-09-01), Huber et al.
patent: 5720431 (1998-02-01), Sellers
patent: 0230917 (1987-08-01), None
patent: 1126135 (2001-08-01), None
patent: 2112868 (1983-07-01), None
patent: 2349920 (2000-11-01), None

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