Part-span shroud configurations

Patent metadata

Field	Value
Publication number	US-2022112811-A1
Application number	US-202017069434-A
Country	US
Kind code	A1
Filing date	Oct 13, 2020
Priority date	Oct 13, 2020
Publication date	Apr 14, 2022
Grant date	—

Abstract

A blade airfoil including a platform, concave pressure sidewall and convex suction sidewall extending axially between corresponding leading and trailing edges and radially between a root and outboard tip. The blade further includes at least one part-span shroud positioned on the airfoil defined by a nominal profile in accordance with at least a portion of Cartesian coordinate values of X, Y and Z set forth in at least one of TABLE I and TABLE II. The Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying values by a length of the at least one part-span shroud. X and Y values are connected by continuing arcs to define part-span shroud profile sections at each distance Z along at least a portion of the at least one part-span shroud, profile sections at Z distances being joined with one another to form the nominal profile.

First claim

1 . A blade, the blade comprising:
an airfoil including a platform, a concave pressure sidewall, and a convex suction sidewall extending axially between corresponding leading and trailing edges and radially between a root and an outboard tip, the blade further including: at least one part-span shroud positioned on the airfoil, the at least one part-span shroud being defined by a nominal profile in accordance with Cartesian coordinate values of X, Y and Z set forth in at least one of TABLE I and TABLE II, wherein the Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the values by a length of the at least one part-span shroud expressed in units of distance, and wherein X and Y values connected by smooth continuing arcs define at least one part-span shroud profile sections at each distance Z along at least a portion of the at least one part-span shroud, the at least one part-span shroud profile sections at the Z distances being joined smoothly with one another to form the nominal profile.

2 . The blade according to claim 1 , wherein the at least one part-span shroud includes an outboard part-span shroud and an inboard part-span shroud, wherein the outboard part-span shroud is defined by the Cartesian coordinate values of TABLE I, and the inboard part-span shroud is defined by the Cartesian coordinate values of TABLE II.

3 . The blade according to claim 2 , wherein the inboard part-span shroud is disposed within a first range of radial distances defined on the airfoil, wherein the first range includes an inboard boundary at 25% of a radial distance of the airfoil and an outboard boundary at 75% of the radial distance of the airfoil; and wherein the outboard part-span shroud is disposed within a second range of radial distances defined on the airfoil, wherein the second range includes an inboard boundary at 60% of the radial distance of the airfoil.

4 . The blade according to claim 2 , wherein each of the outboard part-span shroud and the inboard part-span shroud include an elliptical trailing edge.

5 . The blade according to claim 4 , wherein each elliptical trailing edge is defined by:
x 2 /a 2 +y 2 /b 2 =1, where a represents half the length of the major axis while b represents half the length of the minor axis, and a:b is in a range from about 10:1 to about 1.5:1.

6 . The blade according to claim 5 , wherein a:b is in a range from about 7:1 to about 1.5:1.

7 . The blade according to claim 5 , wherein a:b is in a range from about 5:1 to about 1:1.

8 . The blade according to claim 5 , wherein a:b is about 3:1.

9 . The blade according to claim 1 , where the blade is part of a gas turbine.

10 . A blade, the blade comprising:
an airfoil including a platform, a concave pressure sidewall, and a convex suction sidewall extending axially between corresponding leading and trailing edges and radially between a root and an outboard tip, the blade further including at least one part-span shroud positioned on the airfoil, the trailing edge of the at least one part-span shroud being defined by x 2 /a 2 +y 2 /b 2 =1, where a represents half the length of the major axis while b represents half the length of the minor axis, and a:b is in a range from 10:1 to 1:1; wherein the at least one part-span shroud includes an outboard part-span shroud and an inboard part-span shroud, wherein the outboard part-span shroud is defined by coordinates of TABLE I, and the inboard part-span shroud is defined by coordinates of TABLE II.

11 . The blade according to claim 10 , wherein a:b is in a range from about 7:1 to about 1.5:1.

12 . The blade according to claim 10 , wherein a:b is in a range from about 5:1 to about 1:1.

13 . The blade according to claim 10 , wherein a:b is about 3:1.

14 . (canceled)

15 . The blade according to claim 10 , wherein the blade is part of a gas turbine.

16 . A blade, the blade comprising:
an airfoil including a platform, a concave pressure sidewall, and a convex suction sidewall extending axially between corresponding leading and trailing edges and radially between a root and an outboard tip, the blade further including: an outboard part-span shroud and an inboard part-span shroud positioned on the airfoil, wherein the outboard part-span shroud is defined by a nominal profile in accordance with Cartesian coordinate values of X, Y and Z set forth in TABLE I, and the inboard part-span shroud is defined by a nominal profile in accordance with at least a portion of Cartesian coordinate values of X, Y and Z set forth in TABLE II, wherein the Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the values by a length of each at least one part-span shroud expressed in units of distance, and wherein X and Y values connected by smooth continuing arcs define at least one part-span shroud profile sections at each distance Z along at least a portion of the at least one part-span shroud, the at least one part-span shroud profile sections at the Z distances being joined smoothly with one another to form the nominal profile, and wherein each of the outboard part-span shroud and an inboard part-span shroud include an elliptical trailing edge, and wherein each elliptical trailing edge is defined by: x 2 /a 2 +y 2 /b 2 =1, where a represents half the length of the major axis while b represents half the length of the minor axis.

17 . The blade according to claim 16 , wherein a:b is about 3:1.

18 . The blade according to claim 16 , wherein the blade is part of a gas turbine.

Assignees

• Gen Electric

Inventors

• Ristau Neil Devin
• Wondrasek Michael Anthony

Classifications

• Y02T50/60

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

• F05D2250/74

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

• F01D5/225 Primary

  by shrouding · CPC title

• F01D5/141 Primary

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

• F05D2220/32

  in gas turbines · CPC title