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US 10,480,323 B2Granted
Gas turbine engine turbine blade airfoil profile
AssigneeUnited Technologies Corporation
InventorWolfgang Balzer
Life of this patent
Estimating the term…
Abstract
A turbine blade for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil including leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface extending from a platform in a radial direction to a tip. The external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil described by a set of Cartesian coordinates.
Claims20
A turbine blade for a gas turbine engine comprising:
- an airfoil including leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface extending from a platform in a radial direction to a tip;
- and
- wherein the external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil described by a set of Cartesian coordinates set forth in Table 1, the Cartesian coordinates provided by an axial coordinate scaled by a local axial chord, a circumferential coordinate scaled by a local axial chord, and a span location, wherein the local axial chord corresponds to a width of the airfoil between the leading and trailing edges at the span location.
A turbine section for a gas turbine engine comprising:
- a high pressure turbine configured to drive a compressor section;
- a low pressure turbine configured to drive a fan section;
- wherein the high pressure turbine includes an array of turbine blades, wherein at least one turbine blade includes an airfoil having leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface extending from a platform in a radial direction to a tip;
- and
- wherein the external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil described by a set of Cartesian coordinates set forth in Table 1, the Cartesian coordinates provided by an axial coordinate scaled by a local axial chord, a circumferential coordinate scaled by a local axial chord, and a span location, wherein the local axial chord corresponds to a width of the airfoil between the leading and trailing edges at the span location.
2 more elements
A gas turbine engine comprising:
- a compressor section;
- a combustor fluidly connected to the compressor section;
- a turbine section fluidly connected to the combustor, the turbine section comprising a high pressure turbine coupled to the compressor section via a shaft, and a low pressure turbine aft of the high pressure turbine;
- wherein the high pressure turbine includes an array of turbine blades, wherein at least one turbine blade includes an airfoil having leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface extending from a platform in a radial direction to a tip;
- and
- wherein the external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil described by a set of Cartesian coordinates set forth in Table 1, the Cartesian coordinates provided by an axial coordinate scaled by a local axial chord, a circumferential coordinate scaled by a local axial chord, and a span location, wherein the local axial chord corresponds to a width of the airfoil between the leading and trailing edges at the span location.
3 more elements
Dependencies are inferred from the claim text.