Cooled airfoils for a gas turbine engine

Details Cooled airfoils for a gas turbine engine Cooled airfoils for a gas turbine engine

1994-12-13

1997-12-30

Carone, Michael J.

Fluid reaction surfaces (i.e., impellers)

With heating, cooling or thermal insulation means

416 96R, 416 97R, F01D 518

Patent

active

057022321

ABSTRACT:
An internally cooled airfoil for a gas turbine engine includes a leading edge region, a mid-chord region, a transition region, and a trailing edge region. The mid-chord region has a double wall configuration with the two outer walls and two inner walls. The trailing edge region has a conventional single wall configuration. The transition region has a three wall configuration designed to provide a gradual transition from the four wall configuration to the two wall configuration and to minimize high stresses therein.

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