Ceramic core assembly for serpentine flow circuit in a turbine blade
First Claim
1. A turbine airfoil for use in a gas turbine engine, the turbine airfoil including a leading edge and a trailing edge and a pressure side and a suction side, the turbine airfoil comprising:
- a serpentine flow cooling circuit extending from the leading edge and along the pressure side to the trailing edge, and then extending from the trailing edge along the suction side to a location just downstream from the leading edge, the serpentine flow cooling circuit forming one continuous flow path for cooling air.
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Accused Products
Abstract
A turbine blade for use in a gas turbine engine having an internal serpentine flow cooling circuit with pin fins and trip strips to promote heat transfer for obtaining a thermally balanced blade sectional temperature distribution. The turbine blade is cooled by a 7-pass serpentine flow cooling circuit that extends from the leading edge and along the pressure side wall of the airfoil, into the trailing edge and then flows along the suction side wall ending just downstream from the leading edge where the 7-pass serpentine flow circuit started. Leading edge film cooling holes are supplied from the first leg of the serpentine while a row of trailing edge exit holes is supplied from the third leg which extends across both walls of the airfoil in the trailing edge.
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Citations
10 Claims
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1. A turbine airfoil for use in a gas turbine engine, the turbine airfoil including a leading edge and a trailing edge and a pressure side and a suction side, the turbine airfoil comprising:
a serpentine flow cooling circuit extending from the leading edge and along the pressure side to the trailing edge, and then extending from the trailing edge along the suction side to a location just downstream from the leading edge, the serpentine flow cooling circuit forming one continuous flow path for cooling air. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10)
Specification