Hollow airfoil for a gas turbine engine

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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F01D 518

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061649120

ABSTRACT:
A hollow airfoil is provided which includes a body having an external wall and an internal cavity. The external wall includes a suction side portion and a pressure side portion. The portions extend chordwise between a leading edge and a trailing edge and spanwise between an inner radial surface and an outer radial surface. A stagnation line extends along the leading edge. A plurality of cooling apertures, disposed spanwise along the leading edge. According to one aspect of the present invention, the apertures extend through the external wall along a helical path. According to another aspect of the present invention, the apertures are alternately directed towards the suction side portion and the pressure side portions of the airfoil.

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U.S. application No. 08/992,322, Tabbita et al., filed Dec. 17, 1997.
U.S. application No. 08/992,323, Liang et al., filed Dec. 17, 1997.
U.S. Patent Application Serial No. 08/992,322, filed Dec. 17, 1997, entitled "Apparatus and Method for Cooling an Airfoil for a Gas Turbine Engine", inventors Martin G. Tabbita, James P. Downs, Friedrich O. Soechting and Thomas A. Auxier., pp. 1-15, plus two sheets of drawings, assigned to United Technologies Corporation.
U.S. Patent Application Serial No. 08/992,323, filed Dec. 17, 1997, entitled "Airfoil with Leading Edtge Cooling", inventors George P. Liang and Thomas A. Auxier, pp. 1-9, plus two sheets of drawings, assigned to United Technologies Corporation.
Copy of U.S. Patent Application No. 09/480,956, 15 pages specification/claims/abstract, 2 sheets drawings.

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