Cooled turbine blade for a gas turbine

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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415115, F01D 518

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active

056242310

ABSTRACT:
A turbine blade performs internal cooling by a cooling gas flowing through internal cooling flow passages and FCFC cooling by a cooling gas jetted out through film holes arranged on the substantially whole area of the blade surface. The film holes are arranged in rows extending in the span direction at predetermined pitches in the chord direction. The dimensions of the elements of the turbine blade are determined by a mathematical formula 5.ltoreq.L/N.multidot.D.ltoreq.50, where L is the length of any interval of the surface of the cooled turbine blade, N is the number of rows of the film holes in the interval and D is an average diameter of the film holes in the interval. With this arrangement, the maximum cooling efficiency at a small amount of cooling gas flow is attained, and both the quantity of heat per unit area of the blade surface transmitted from the main flow gas to the blade surface and the thermal stresses are reduced.

REFERENCES:
patent: 4118146 (1978-10-01), Dierberger
patent: 4676719 (1987-06-01), Auxier et al.
patent: 4767261 (1988-08-01), Godfrey et al.
patent: 5120192 (1992-06-01), Ohtomo et al.
patent: 5374162 (1994-12-01), Green
patent: 5392515 (1995-02-01), Auxier et al.
patent: 5417545 (1995-05-01), Harrogate
patent: 5419681 (1995-05-01), Lee

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