Turbine vane structure

Rotary kinetic fluid motors or pumps – With changing state confined heat exchange mass

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Details

416 96R, F01D 518, F01D 902

Patent

active

042181780

ABSTRACT:
A liquid cooled stator blade assembly for a gas turbine engine includes an outer shroud having a pair of liquid inlets and a pair of liquid outlets supplied through a header and wherein means including tubes support the header radially outwardly of the shroud and also couple the header with the pair of liquid inlets and outlets. A pair of turbine vanes extend radially between the shroud and a vane platform to define a gas turbine motive fluid passage therebetween; and each of the vanes is cooled by an internal body casting of super alloy material with a grooved layer of highly heat conductive material that includes spaced apart flat surface trailing edges in alignment with a flat trailing edge of the casting joined to wall segments of the liner which are juxtaposed with respect to the internal casting to form an array of parallel liquid inlet passages on one side of the vane and a second plurality of parallel liquid return passages on the opposite side of the vane; and a superalloy heat and wear resistant imperforate skin covers the outer surface of the composite blade including the internal casting and the heat conductive layer; a separate trailing edge section includes an internal casting and an outer skin butt connected to the end surfaces of the internal casting and the heat conductive layer to form an easily assembled liquid cooled trailing edge section in the turbine vane.

REFERENCES:
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patent: 3075744 (1963-01-01), Peterson
patent: 3172621 (1963-07-01), Erwin
patent: 3443790 (1969-05-01), Buckland
patent: 3446481 (1969-05-01), Kydd
patent: 3515499 (1970-06-01), Beer et al.
patent: 3610769 (1971-10-01), Schwedland
patent: 3650635 (1972-03-01), Wachtell et al.
patent: 3658439 (1972-04-01), Kydd
patent: 3732031 (1973-05-01), Bowling et al.
patent: 4127358 (1978-11-01), Parkes
patent: 4156582 (1979-05-01), Anderson

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