CONFIGURATIONS FOR TURBINE ROTOR BLADE TIPS

• US 20170058680A1
• Filed: 09/02/2015
• Published: 03/02/2017
• Est. Priority Date: 09/02/2015
• Status: Abandoned Application

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Chouhan, Rohit, Jaiswal, Shashwat Swami
• Application Number:
  US14/843,069
• Publication Number:
  US 20170058680A1
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: F01D 5/18 Hollow blades, i.e. blades with cooling or heating channels or cavities structure of hollow blades in general F01D5/147; Heating, heat-insulating or cooling means on blades
• CPC Class Codes: F01D 5/20 Specially-shaped blade tips to seal space between tips and stator F01D5/225 takes precedence
• CPC Class Codes: F05D 2220/32 in gas turbines
• CPC Class Codes: F05D 2240/306 related to the suction side of a rotor blade
• CPC Class Codes: F05D 2240/307 related to the tip of a rotor blade
• CPC Class Codes: F05D 2260/221 Improvement of heat transfer
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A rotor blade for a turbine of a gas turbine system. The rotor blade may include: an airfoil that includes a pressure sidewall and a suction sidewall defining an outer periphery, wherein the pressure sidewall and suction sidewall of the airfoil connect along a leading edge and a trailing edge; a tip that defines an outer radial end of the airfoil, wherein the tip included a cap on which an outboard projecting rail defines a tip cavity; and a rail gap formed through an aftward section of the rail.

Claims

1. A rotor blade for a turbine of a gas turbine system, the rotor blade comprising an airfoil that includes a pressure sidewall and a suction sidewall defining an outer periphery;

wherein the pressure sidewall and suction sidewall of the airfoil connect along a leading edge and a trailing edge, and extend radially between a root and a tip;

wherein the tip defines an outer radial end of the airfoil, the tip including a cap from which an outboard projecting rail defines a tip cavity;

wherein the airfoil includes a winglet positioned near the tip of the airfoil; and

wherein a rail gap is formed through an aftward section of the rail.

2. The rotor blade according to claim 1, wherein the rail includes a pressure rail and a suction rail that correspond, respectively, to the pressure sidewall and the suction sidewall of the airfoil;

wherein the winglet is formed on the suction sidewall; and

wherein the rail gap is formed through the suction rail.

3. The rotor blade according to claim 2, wherein the suction rail comprises a truncated rail that extends between a position near the leading edge of the airfoil and a position removed a predetermined distance from the trailing edge of the airfoil, the predetermined distance corresponding to a width of the rail gap;

wherein the pressure rail comprises an uninterrupted rail that extends continuously between a position near the leading edge of the airfoil and a position near the trailing edge of the airfoil; and

wherein the winglet comprises a radial section of the airfoil in which the suction sidewall angles outwardly with respect to the radial direction.

4. The rotor blade according to claim 2, wherein the suction rail comprises a truncated rail that extends between a position at the leading edge of the airfoil and a position removed a predetermined distance from the trailing edge of the airfoil, the predetermined distance corresponding to a width of the rail gap;

and

wherein the pressure rail comprises an uninterrupted rail that extends continuously between a position at the leading edge of the airfoil and a position at the trailing edge of the airfoil; and

wherein the winglet comprises a radial section of the airfoil in which the suction sidewall angles outwardly with respect to the radial direction.

5. The rotor blade according to claim 4, wherein the suction rail and the pressure rail connect at the leading edge of the airfoil;

wherein the winglet is configured such that the tip cavity widens as the tip cavity extends in an outboard direction between the cap and an outboard rail surface of the rail;

wherein the rail gap is defined between a leading boundary and a trailing boundary, wherein;

the leading boundary of the rail gap comprises a trailing end of the truncated suction rail; and

the trailing boundary of the rail gap comprises a trailing end of the uninterrupted pressure rail.

6. The rotor blade according to claim 5, wherein the pressure rail extends aftward from the leading edge of the airfoil along a path that approximately aligns with a profile of the pressure sidewall;

and

wherein the suction rail extends aftward from the leading edge of the airfoil along a path that approximately aligns with a profile of the suction sidewall.

7. The rotor blade according to claim 6, wherein the cap is configured to extend axially and circumferentially to connect the outer radial edge of the suction sidewall to the outer radial edge of the pressure sidewall;

and

wherein the rail is disposed at a periphery of the cap.

8. The rotor blade according to claim 7, further comprising:

a cooling passage defined through the airfoil; and

outlet ports in fluid communication with the cooling passage, the outlet ports disposed through at least one of the cap, the pressure sidewall and the suction sidewall of the airfoil.

9. The rotor blade according to claim 8, wherein the cooling passage is configured for circulating coolant through an interior of the airfoil during operation, the cooling passage extending radially between a connecting channel formed through the root of the rotor blade and a connection with each of the outlet ports;

and

wherein the tip comprises a squealer tip.

10. The rotor blade according to claim 8, wherein the cap forms a floor of the tip cavity;

wherein the cap comprises a plurality of the outlet ports, the plurality of outlet ports formed through a thickness of the cap so to direct coolant expelled therefrom into the tip cavity formed on the cap; and

wherein the pressure sidewall comprises a plurality of the outlet ports.

11. The rotor blade according to claim 5, wherein the rail includes an inner rail surface, which faces inwardly and defines the tip cavity, an outer rail surface, which opposes the inner rail surface so to face outwardly, and an outboard rail surface that faces in an outboard direction;

and

wherein the rail gap comprises;

a gap through the thickness of the rail that extends from an opening formed on the outer rail surface to an opening formed on the inner rail surface; and

a gap extending radially from an inboard boundary that is approximately coplanar to an outboard surface of the tip cap.

12. The rotor blade according to claim 2, wherein the rail gap comprises a section truncated from the suction rail.

13. The rotor blade according to claim 12, wherein the section truncated from the suction rail comprises between 0% and 40% of a chordwise length of the suction rail.

14. The rotor blade according to claim 12, wherein the section truncated from the suction rail comprises between 10% and 30% of a chordwise length of the suction rail.

15. The rotor blade according to claim 12, wherein the section truncated from the suction rail comprises approximately 20% of a chordwise length of the suction rail.

16. The rotor blade according to claim 14, wherein the winglet comprises a radial section of the airfoil in which the suction sidewall angles outwardly with respect to the radial direction.

17. The rotor blade according to claim 16, wherein the winglet includes an outwardly flaring radial section of the outer wall of the airfoil in which an inboard boundary having a smaller circumference transitions to an outboard boundary having a larger circumference;

and

wherein the winglet comprises a concave contour between the inboard boundary and the outboard boundary of the radial section.

18. The rotor blade according to claim 16, wherein the radial section of the winglet approximately coincides with a radial height of the suction rail such that:

an inboard boundary of the winglet is approximately coplanar to the cap; and

an outboard boundary of the winglet is approximately coplanar to an outboard rail surface of the suction rail.

19. The rotor blade according to claim 16, wherein the winglet extends between a leading end and a trailing end;

wherein the leading end of the winglet is positioned approximately 20% to 40% of a chordwise distance from the leading edge, and the trailing end is positioned approximately 70% to 90% of the chordwise distance from the leading edge; and

wherein the trailing end of the winglet comprise the leading boundary of the rail gap.

20. A combustion turbine engine having rotor blades arranged in a row about a central axis in the turbine;

wherein each of the rotor blades comprises;

an airfoil that includes a pressure sidewall and a suction sidewall defining an outer periphery, wherein the pressure sidewall and suction sidewall of the airfoil connect along a leading edge and a trailing edge, and extend radially between a root and a tip, wherein the tip defines an outer radial end of the airfoil, the tip including a cap from which an outboard projecting rail defines a tip cavity;

wherein the rail includes a pressure rail and a suction rail that correspond, respectively, to the pressure sidewall and the suction sidewall of the airfoil;

a winglet that is positioned near the tip of the airfoil and formed on the suction sidewall; and

a rail gap that is formed through an aftward section of the suction rail, wherein the rail gap comprises a section truncated from the suction rail that comprises between 10% and 30% of a chordwise length of the suction rail.