Turbine blade having tip slot

Details Turbine blade having tip slot Turbine blade having tip slot

1994-12-19

1996-04-02

Look, Edward K.

Fluid reaction surfaces (i.e., impellers)

With fluid passage in working member communicating with...

Both inlet and outlet to working fluid

416 97R, 4151731, F01D 518

Patent

active

055035272

ABSTRACT:
A gas turbine engine rotor blade includes an airfoil having first and second sidewalls joined together at leading and trailing edges. First and second tip walls extend from adjacent the leading edge along the respective first and second sidewalls to adjacent the trailing edge and are spaced apart to define a tip cavity therebetween. A first notch is disposed in the first tip wall adjacent to the leading edge for channeling into the tip cavity a portion of combustion gases flowable over the airfoil for reducing the heating effect of the gases on the blade tip. In a preferred embodiment, a second notch is disposed adjacent to the trailing edge for promoting flow through the tip cavity from the first notch.

REFERENCES:
patent: 3635585 (1972-01-01), Metzler, Jr.
patent: 3885886 (1975-05-01), Richter
patent: 4010531 (1977-03-01), Andersen et al.
patent: 4390320 (1983-06-01), Eiswerth
patent: 4424001 (1984-01-01), North et al.
patent: 4761116 (1988-08-01), Braddy et al.
patent: 5176499 (1993-01-01), Damlis et al.
patent: 5183385 (1993-02-01), Lee et al.
patent: 5246340 (1993-09-01), Winstanley et al.
patent: 5403158 (1995-04-01), Auxier

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