Fluid reaction surfaces (i.e. – impellers) – Specific blade structure – Radial flow devices
Patent
1997-06-27
1999-11-09
Verdier, Christopher
Fluid reaction surfaces (i.e., impellers)
Specific blade structure
Radial flow devices
416 92, 416 97R, 416193A, 416241R, 416DIG5, F01D 514, F01D 518
Patent
active
059802090
ABSTRACT:
A first-stage turbine blade includes an airfoil having a profile according to Table I. The airfoil has a plurality of cooling air passages extending linearly from the root portion to the tip portion of the airfoil. The blade includes a shank having a pair of cavities in communication through the blade dovetail with a plenum in the wheel space for supplying cooling air to the passages in the airfoil. The cooling passages in the airfoil terminate in a recess at the tip portion which has an opening adjacent the trailing edge of the airfoil and along the suction side to enable egress of cooling air into the hot gas stream on the low pressure side of the airfoil. The majority of the cooling passages are turbulated. Certain of those passages are arranged in rows lying adjacent to the pressure and suction sides of the airfoil.
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"Gas Turbine Engine with Air-Cooled Blading", The Oil Engine and Gas Turbine, Issue 240, pp. 70-72, Jun. 1953.
Abuaf Nesim
Barry Vincent Anthony
Gregory Brent A.
General Electric Co.
Verdier Christopher
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