Gas turbine engine turbine blade airfoil profile

Patent metadata

Field	Value
Publication number	US-10480323-B2
Application number	US-201614993528-A
Country	US
Kind code	B2
Filing date	Jan 12, 2016
Priority date	Jan 12, 2016
Publication date	Nov 19, 2019
Grant date	Nov 19, 2019

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.

First claim

What is claimed is:

1. 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.

2. The turbine blade according to claim 1 , wherein the airfoil is a second stage turbine blade.

3. The turbine blade according to claim 1 , wherein the span location corresponds to a distance from a rotational axis of the airfoil.

4. The turbine blade according to claim 1 , wherein the Cartesian coordinates in Table 1 have a tolerance relative to the specified coordinates of ±0.030 inches (±0.762 mm).

5. 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.

6. The gas turbine engine according to claim 5 , wherein the array is a second stage array of turbine blades.

7. The gas turbine engine according to claim 6 , wherein the high pressure turbine includes an array of fixed stator vanes upstream from the first stage array of turbine blades.

8. The gas turbine engine according to claim 6 , wherein the second stage array of turbine blades includes forty-four turbine blades.

9. The gas turbine engine according to claim 5 , wherein the span location corresponds to a distance from a rotational axis of the airfoil.

10. The gas turbine engine according to claim 5 , wherein the Cartesian coordinates in Table 1 have a tolerance relative to the specified coordinates of ±0.030 inches (±0.762 mm).

11. The gas turbine engine according to claim 5 , wherein the high pressure turbine includes two arrays of turbine blades and two arrays of fixed stator vanes.

12. 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.

13. The gas turbine engine according to claim 12 , wherein the array is a second stage array of turbine blades.

14. The gas turbine engine according to claim 13 , wherein the high pressure turbine includes an array of fixed stator vanes upstream from the first stage array of turbine blades.

15. The gas turbine engine according to claim 13 , wherein the second stage array of turbine blades includes forty-four turbine blades.

16. The gas turbine engine according to claim 12 , wherein the span location corresponds to a distance from a rotational axis of the airfoil.

17. The gas turbine engine according to claim 12 , wherein the Cartesian coordinates in Table 1 have a tolerance relative to the specified coordinates of ±0.030 inches (±0.762 mm).

18. The gas turbine engine according to claim 12 , wherein the high pressure turbine includes two arrays of turbine blades and two arrays of fixed stator vanes.

19. The gas turbine engine according to claim 12 , wherein the low pressure turbine includes between three and six stages of turbine blades.

20. The gas turbine engine according to claim 12 , comprising:
a fan section including a plurality of fan blades; and
a geared architecture configured to cause the fan section to rotate at a lower speed than the low pressure turbine.

Assignees

• United Technologies Corp

Inventors

• Balzer Wolfgang

Classifications

• F01D5/141 Primary

  Shape, i.e. outer, aerodynamic form (F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147) · CPC title

• F05D2250/74

  given by a set or table of xyz-coordinates · CPC title

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title