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US 7,726,944 B2Granted
Turbine blade with improved durability tip cap
AssigneeUnited Technologies Corporation
InventorsRichard H. Page, Wieslaw A. Chlus
Life of this patent
Estimating the term…
Abstract
A gas turbine engine has a turbine blade having a tip cap to close off internal cooling passages. The tip cap is formed with a plurality of purge holes, with there being at least two rows of purge holes. The increased number of purge holes spreads the cooling air outwardly across more of the surface area of the tip cap, and provides the tip cap with a better ability to withstand the extreme temperatures it faces in use.
Claims12
A tip cap for a gas turbine engine turbine blade comprising:
- a plurality of purge holes to allow air from cooling channels in said turbine blade to move outwardly through said tip cap and radially outwardly of said turbine blade, said purge holes being formed in at least two rows at distinct locations between a suction side and a pressure side of said turbine blade;
- said tip cap including two portions having only one row of purge holes with a first spaced toward a leading edge of said turbine blade, and a second toward a trailing edge of said turbine blade and from a central portion of said tip cap having said at least two rows of purge holes;
- and
- there being at least two diameters to said purge holes.
1 more element
A turbine blade for a gas turbine engine comprising:
- a platform with an airfoil extending radially outwardly from said platform, said airfoil including internal cooling channels, said cooling channels routing air from a location adjacent said platform radially outwardly towards a tip of said airfoil, and said tip of said airfoil including a support recess for receiving a separate tip cap, said tip cap closing off said cooling channels, and said tip cap including a plurality of purge holes to allow air from said cooling channels to move outwardly through said tip cap and radially outwardly of said airfoil, said purge holes being formed in at least two rows at distinct locations between a suction side and a pressure side of said airfoil;
- said tip cap including two portions having only one row of purge holes with a first spaced toward a leading edge of said turbine blade, and a second toward a trailing edge of said turbine blade and from a central portion of said tip cap having said at least two rows of purge holes;
- and
- there being at least two diameters to said purge holes.
1 more element
Dependencies are inferred from the claim text.