Power turbine blades in gas turbine engines

Patent metadata

Field	Value
Publication number	US-12529318-B1
Application number	US-202519089903-A
Country	US
Kind code	B1
Filing date	Mar 25, 2025
Priority date	Feb 26, 2025
Publication date	Jan 20, 2026
Grant date	Jan 20, 2026

Abstract

A power turbine blade for a gas turbine engine includes at least one of a third-stage blade, a fourth-stage blade, or a fifth-stage blade. The power turbine blade includes a platform and an airfoil that extends in a spanwise direction from the platform to a tip shroud. The airfoil has an external airfoil surface formed in conformance with multiple cross-section airfoil profiles described by a set of Cartesian coordinates.

First claim

What is claimed is:

1 . A power turbine blade for a gas turbine engine, the power turbine blade comprising:
an airfoil having a leading edge and a trailing edge joined by a pressure side and a suction side to provide an external airfoil surface configured to extend from a platform in a spanwise direction to a tip; and wherein the external airfoil surface is formed in conformance with multiple cross-section profiles of the airfoil described by a set of Cartesian coordinates set forth in one of Tables 1 to 3, the Cartesian coordinates provided by an axial coordinate scaled by a local axial chord, a circumferential coordinate scaled by the local axial chord, and a span location, wherein the local axial chord corresponds to a width of the airfoil between the leading edge and the trailing edge at the span location.

2 . The power turbine blade according to claim 1 , wherein the power turbine blade is a third-stage blade and the external airfoil surface is formed in conformance with multiple cross-section profiles of the airfoil described by the set of Cartesian coordinates set forth in Table 1.

3 . The power turbine blade according to claim 1 , wherein the power turbine blade is a fourth-stage blade and the external airfoil surface is formed in conformance with multiple cross-section profiles of the airfoil described by the set of Cartesian coordinates set forth in Table 2.

4 . The power turbine blade according to claim 1 , wherein the power turbine blade is a fifth-stage blade and the external airfoil surface is formed in conformance with multiple cross-section profiles of the airfoil described by the set of Cartesian coordinates set forth in Table 3.

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

6 . The power turbine blade according to claim 1 , wherein the Cartesian coordinates in each of Tables 1 to 3 have a tolerance relative to the specified coordinates of ±0.004 inches.

7 . The power turbine blade according to claim 1 , wherein the Cartesian coordinates in each of Tables 1 to 3 have a tolerance relative to the specified coordinates of ±0.05 inches.

8 . The power turbine blade according to claim 1 , wherein the external airfoil surface includes an uncoated airfoil surface, and wherein the Cartesian coordinates define points on the uncoated airfoil surface at nominal restagger, in a plane at the span location.

9 . A power turbine blade for a gas turbine engine, the power turbine blade including at least one of a third-stage blade, a fourth-stage blade, or a fifth-stage blade, the power turbine blade comprising:
a platform; and an airfoil extending in a spanwise direction from the platform to a tip, the airfoil having an external airfoil surface formed in conformance with multiple cross-section airfoil profiles described by a set of Cartesian coordinates set forth in one of Tables 1 to 3.

10 . The power turbine blade according to claim 9 , wherein the external airfoil surface includes an uncoated airfoil surface, and wherein the Cartesian coordinates in each of Tables 1 to 3 have Cartesian coordinate values for the uncoated condition at nominal restagger.

11 . The power turbine blade according to claim 9 , wherein the Cartesian coordinates in each of Tables 1 to 3 have a tolerance relative to the specified coordinates of ±0.004 inches.

12 . The power turbine blade according to claim 9 , wherein the Cartesian coordinates in each of Tables 1 to 3 have a tolerance relative to the specified coordinates of ±0.05 inches.

13 . A gas turbine engine comprising:
a power turbine blade having an array of airfoils, wherein at least one airfoil of the array of airfoils has a leading edge and a trailing edge that are joined by spaced-apart pressure and suction sides to provide an external airfoil surface extending from a platform in a span direction to a tip shroud; and wherein the external airfoil surface is formed in conformance with multiple cross-section profiles of the at least one airfoil described by a set of Cartesian coordinates set forth in one of Tables 1 to 3, the Cartesian coordinates provided by an axial coordinate scaled by a local axial chord, a circumferential coordinate scaled by the local axial chord, and a span location, wherein the local axial chord corresponds to a width of the at least one airfoil between the leading edge and the trailing edge at the span location.

14 . The gas turbine engine according to claim 13 , wherein the span location corresponds to a distance from a rotation axis of the at least one airfoil.

15 . The gas turbine engine according to claim 13 , wherein the Cartesian coordinates in each of Tables 1 to 3 have a tolerance relative to the specified coordinates of ±0.004 inches.

16 . The gas turbine engine according to claim 13 , wherein the Cartesian coordinates in each of Tables 1 to 3 have a tolerance relative to the specified coordinates of ±0.05 inches.

17 . The gas turbine engine according to claim 13 , wherein the external airfoil surface includes an uncoated airfoil surface, and wherein the Cartesian coordinates define points on the uncoated airfoil surface of the at least one airfoil at nominal restagger, in a plane at the span location.

18 . The gas turbine engine according to claim 13 , wherein the power turbine blade is at least one of a third-stage blade, a fourth-stage blade, or a fifth-stage blade.

Assignees

• Ge Aerospace Poland Sp Z O O
• Ge Avio Srl

Inventors

• Szymański Łukasz
• Zareba Piotr
• Karpiński Grzegorz
• Bujak Michał Mateusz
• Staszyński Wojciech Łukasz
• Lizzer Cristian

Classifications

• F01D9/041

  using blades (F01D5/148 takes precedence) · CPC title

• F02C7/00

  Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants (controlling F02C9/00) · CPC title

• F05D2250/74

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

• F01D5/141 Primary

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

• Y02T50/60

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