Turbine blade having recuperative trailing edge tip cooling

Details Turbine blade having recuperative trailing edge tip cooling Turbine blade having recuperative trailing edge tip cooling

1997-09-29

1999-07-27

Lopez, F. Daniel

Fluid reaction surfaces (i.e., impellers)

With heating, cooling or thermal insulation means

Changing state mass within or fluid flow through working...

416 92, 416224, 416231R, 415115, F01D 518

Patent

active

059279460

ABSTRACT:
A gas turbine engine rotor blade includes an airfoil having a concave side wall and a convex side wall joined together at leading and trailing edges. Concave and convex tip walls extend from adjacent the leading edge along the respective concave and convex side walls to adjacent the trailing edge and are spaced apart to define a tip cavity therebetween. A hole or channel is disposed in a trailing edge tip region connecting the tip cavity to the trailing edge for channeling cooling fluid through the trailing edge tip region.

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