Blades having tip pockets

Patent metadata

Field	Value
Publication number	US-11168569-B1
Application number	US-202016851371-A
Country	US
Kind code	B1
Filing date	Apr 17, 2020
Priority date	Apr 17, 2020
Publication date	Nov 9, 2021
Grant date	Nov 9, 2021

Abstract

A rotor blade for use in a turbine of a combustion turbine engine comprises an airfoil, which includes a concave pressure and convex suction sidewall extending axially between corresponding leading and trailing edges and radially between base and outboard tip end. The rotor blade further including at least one mid-span shroud engages a corresponding mid-span shroud on at least one neighboring rotor blade. The airfoil includes an inboard region between the at least one mid-span shroud and base of the blade—and an outboard region between at least one mid-span shroud and outward tip. The outboard region includes at least two cavities extending from the outboard tip end inboard toward the at least one mid-span shroud; and inboard of the at least one mid-span shroud, the inboard region is substantially solid.

First claim

What is claimed:

1. A rotor blade for use in a turbine of a combustion turbine engine, the rotor blade comprising:
an airfoil, the airfoil including a concave pressure sidewall and a convex suction sidewall extending axially between corresponding leading and trailing edges and radially between a base and an outboard tip end, the rotor blade further including:
at least one mid-span shroud configured to engage a corresponding mid-span shroud on at least one neighboring rotor blade during operation;
the airfoil further including an inboard region between the at least one mid-span shroud and the base of the blade with an inboard direction of the airfoil toward the base;
the airfoil further including an outboard region between the at least one mid-span shroud and an outboard tip end of the blade with an outboard direction of the airfoil toward the outboard tip end;
wherein:
i. the outboard region includes at least two cavities extending from the outboard tip end inboard of the airfoil toward the at least one mid-span shroud, wherein the at least two cavities include sidewalls and bottom walls, each respective bottom wall of the at least two cavities being at different angles respect to each other and the sidewalls; and
ii. inboard of the at least one mid-span shroud, the inboard region is substantially solid.

2. The rotor blade of claim 1 , wherein the bottom walls extending different distances into the airfoil.

3. The rotor blade of claim 1 , wherein the bottom walls are non-orthogonal to the sidewalls.

4. The rotor blade of claim 1 , wherein the at least two cavities include varying cross sections.

5. The rotor blade of claim 4 , wherein the varying cross sections are formed by a depth of the cavities along the sidewalls of the at least two cavities.

6. The rotor blade of claim 1 , wherein the at least two cavities are open at the outboard tip end and closed at their inboard ends.

7. The rotor blade of claim 1 , wherein the at least two cavities include more than two cavities formed along a chord of the blade.

8. The rotor blade of claim 1 , wherein, at the outboard tip end, the at least two cavities extend up to 60% of the outboard tip end from the leading edge to the trailing edge.

9. The rotor blade of claim 1 , wherein the at least two cavities define a stiffening rib therebetween.

10. The rotor blade of claim 1 , wherein the at least two cavities are entirely in the outboard region above the at least one mid-span shroud.

11. The rotor blade of claim 1 , wherein the outboard region has hollowness percentage of at least 40% and wherein the inboard region has a solidness percentage of at least 60%.

12. A combustion turbine engine, the combustion turbine engine comprising:
a rotor blade including an airfoil, the airfoil including a concave pressure sidewall and a convex suction sidewall extending axially between corresponding leading and trailing edges; a base and an outboard tip end, the rotor blade further including:
at least one mid-span shroud configured to engage a corresponding mid-span shroud on at least one neighboring rotor blade during operation;
the airfoil further including an inboard region between the at least one mid-span shroud and the base of the blade with an inboard direction of the airfoil toward the base;
the airfoil further including an outboard region between the at least one mid-span shroud and an outboard tip end of the blade with an outboard direction of the airfoil toward the outboard tip end;
wherein:
i. the outboard region includes at least two cavities extending from the outboard tip end inboard of the airfoil toward the at least one mid-span shroud, wherein the at least two cavities include sidewalls and bottom walls, each respective bottom wall of the at least two cavities being at different angles respect to each other and the sidewalls; and inboard of the at least one mid-span shroud, the inboard region is substantially solid.

13. The combustion turbine engine of claim 12 , wherein the outboard region being substantially hollow is defined as the outboard region having a hollowness percentage of at least 70% and wherein the inboard region being substantially solid is defined as the inboard region having a solidness percentage of at least 90%.

14. The combustion turbine engine of claim 12 , wherein the at least two cavities include more than two cavities.

15. The combustion turbine engine of claim 12 , wherein the at least two cavities are entirely in the outboard region.

16. The combustion turbine engine of claim 12 , wherein the bottom walls extending different distances into the airfoil.

17. The combustion turbine engine of claim 12 , wherein the at least two cavities include more than two cavities formed along a chord of the blade.

18. The combustion turbine engine of claim 12 , wherein the bottom walls are non-orthogonal to the sidewalls.

19. A combustion turbine engine, the combustion turbine engine comprising:
a rotor blade including an airfoil, the airfoil including a concave pressure sidewall and a convex suction sidewall extending axially between corresponding leading and trailing edges; a base and an outboard tip end, the rotor blade further including a midsection area:
the airfoil further including an inboard region between the midsection area and the base of the blade with an inboard direction of the airfoil toward the base;
the airfoil further including an outboard region between the midsection area and an outboard tip end of the blade with an outboard direction of the airfoil toward the outboard tip end;
wherein:
i. the outboard region includes at least two cavities extending from the outboard tip end inboard of the airfoil toward the midsection area, wherein the at least two cavities include sidewalls and bottom walls, each respective bottom wall of the at least two cavities being at different angles respect to each other and the sidewalls; and inboard of midsection area, the inboard region is substantially solid.

Assignees

• Gen Electric

Inventors

• Ristau Neil Devin
• Wondrasek Michael Anthony

Classifications

• F01D5/16

  for counteracting blade vibration · CPC title

• F01D5/147 Primary

  Construction, i.e. structural features, e.g. of weight-saving hollow blades (F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18) · CPC title

• Y02T50/60

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

• F05D2260/96

  Preventing, counteracting or reducing vibration or noise · CPC title

• F05D2240/307

  related to the tip of a rotor blade · CPC title