Blade cooling passage for a turbine engine

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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Reexamination Certificate

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07845907

ABSTRACT:
A blade for a turbine engine includes structure providing spaced apart suction and pressure sides. A cooling passage includes a first passageway near the pressure side and a second passageway in fluid communication with the first passageway. The second passageway is arranged between the first passageway and the suction side. The cooling passage provides a serpentine cooling path that is arranged in a direction transverse from a chord extending between trailing and leading edges of the blade. During use, cooling fluid is supplied to the pressure side through first cooling apertures fluidly connected to the first passageway to the suction side through second cooling apertures fluidly connected to the other passage way. The first passageway is at a higher pressure that then second passageway so that cooling fluid is provided by the cooling passage to the pressure and suction sides in a balanced fashion.

REFERENCES:
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patent: 5538394 (1996-07-01), Inomata et al.
patent: 6402471 (2002-06-01), Demers et al.
patent: 7377746 (2008-05-01), Brassfield et al.
patent: 7481622 (2009-01-01), Liang
patent: 2003/0075300 (2003-04-01), Shah et al.
patent: 05195704 (1993-08-01), None
JP 5-195704 Machine Translation. http://www4.ipdl.inpit.go.jp/Tokujitu/tjsogodben.ipdl?N0000=115. Search terms: Kind Code: A, No. H05-195704. Accessed Mar. 31, 2010.

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