Cooling arrangement for gas turbine blade platform
AssigneeSiemens Energy, Inc.
InventorsCharles M. Evans, Andrew R. Narcus, Robert J. McClelland, Frank Moehrle
Life of this patent
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Abstract
A gas turbine engine blade (10), having: an airfoil (12) having a pressure side (22) and a suction side (24); an inner platform (30), having: a gas path surface (40); a coolant surface (42); and at least one row (114) of film cooling holes (112) spanning there between and disposed on the pressure side of the airfoil. The film cooling holes are angled to include a directional component substantially parallel with the pressure side at a trailing end of the airfoil, and the at least one row is oriented substantially parallel to a mateface wall (122) of the inner platform. An array (130) of turbulators (132) is disposed on the coolant surface.
Claims20
A gas turbine engine blade, comprising:
- an airfoil comprising a pressure side and a suction side;
- an inner platform, comprising:
- a gas path surface;
- a coolant surface;
- and at least one row of film cooling holes spanning there between and disposed on the pressure side of the airfoil, the film cooling holes angled to comprise a directional component parallel with the pressure side at a trailing end of the airfoil, and the at least one row is oriented parallel to a mateface wall of the inner platform;
- and
- an array of turbulators disposed on the coolant surface.
In a gas turbine engine blade comprising:
- an airfoil comprising a pressure side and a suction side;
- an inner platform comprising a gas path surface, a coolant surface, and a mateface wall;
- and a shank;
- wherein the shank, the coolant surface, and the mateface wall define a shank pocket, an improvement comprising:
- at least one row of film cooling holes spanning between the gas path surface and the coolant surface and disposed on a pressure side of the airfoil, wherein the at least one row parallel to the mateface wall;
- a shank cooling hole spanning between a mateface of the shank and an internal cooling supply channel within the shank, the shank cooling hole configured to direct a shank impingement jet onto the mateface wall at an impingement location;
- and
- a mateface purge slot through the mateface wall aft of the impingement location,
- wherein the gas turbine engine blade is configured such that during operation spent impingement air flows radially outward into the shank pocket, and the shank cooling pocket supplies cooling fluid to the film cooling holes and the mateface purge slot.
Dependencies are inferred from the claim text.