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US 7,837,441 B2Granted
Impingement skin core cooling for gas turbine engine blade
AssigneeUnited Technologies Corporation
InventorsBrandon W. Spangler, Dominic J. Mongillo, Jr., Michael F. Blair
Life of this patent
Estimating the term…
Abstract
Turbine components, and in particular turbine blades, are provided with impingement cooling channels. Air is delivered along central channels, and the central channels deliver the air through crossover holes to core channels adjacent both a pressure wall and a suction wall. The air passing through the crossover holes impacts against a wall of the core channels.
Claims16
A gas turbine engine component comprising:
- a platform and an airfoil extending outwardly of the platform, the airfoil having a suction wall and a pressure wall;
- a plurality of central channels received within said airfoil and extending from said platform outwardly toward a tip of said airfoil;
- said central channels each being provided with plural crossover holes for directing cooling air to at least one core channel associated with each of the pressure and suction walls, and a supply to supply air to the central channels, through said crossover holes, and against a wall of said core channels;
- skin cooling holes formed in said pressure and suction walls, such that the air can pass through the skin cooling holes from said core channels;
- and
- said core channels being supplied entirely from said central channel, with said core channels extending from a closed bottom wall to a top wall, with said cross-over holes supplying the impingement air into said core channels.
3 more elements
A turbine blade comprising:
- a platform and an airfoil extending outwardly of the platform, the airfoil having a suction wall and a pressure wall;
- a plurality of central channels received within said airfoil and extending from said platform outwardly toward a tip of said airfoil;
- said central channels each being provided with plural crossover holes for directing cooling air to at least one core channel associated with each of said pressure and suction walls, and a supply to supply air received within the central channels through said crossover holes, and against a wall of said core channels;
- skin cooling holes formed in said pressure and suction walls, such that the air can leave the skin cooling holes;
- said crossover holes extending for a lesser dimension than do either said central channel or said core channel measured along a distance from a leading edge of said airfoil towards a trailing edge;
- and
- said core channels being supplied entirely from said central channel, with said core channels extending from a closed bottom wall to a top wall, with said cross-over holes supplying the impingement air into said core channels.
4 more elements
A gas turbine engine component comprising:
- a platform and an airfoil extending outwardly of the platform, the airfoil having a suction wall and a pressure wall;
- a plurality of central channels received within said airfoil and extending from said platform outwardly toward a tip of said airfoil;
- said central channels each being provided with plural crossover holes for directing cooling air to at least one core channel associated with at least one of the pressure and suction walls, and a supply to supply air to the central channels, through said crossover holes, and against a wall of said core channels;
- and
- skin cooling holes formed in said pressure and suction walls, such that the air can pass through the skin cooling holes from said at least one core channel, and said at least one core channel being supplied entirely from said central channels, with said at least one core channel extending from a closed bottom wall to a top wall, with said cross-over holes supplying the impingement air into said at least one core channel.
2 more elements
A gas turbine engine component comprising:
- a body;
- a plurality of central channels received within said body;
- said central channels each being provided with plural crossover holes for directing cooling air to at least one core channel associated with walls of the body, and a supply to supply air to the central channels, through said crossover holes, and against one of said wall;
- and
- skin cooling holes formed in said pressure and suction walls, such that the air can pass through the skin cooling holes from said at least one core channel, and said at least one core channel being supplied entirely from said central channels, with said at least one core channel extending from a closed bottom wall to a top wall, with said cross-over holes supplying the impingement air into said at least one core channel.
2 more elements
Dependencies are inferred from the claim text.