Turbine blade cooling with a hollow airfoil configured to minimize a distance between a pin array section and the trailing edge of the air foil

• US 8,231,329 B2
• Filed: 12/30/2008
• Issued: 07/31/2012
• Est. Priority Date: 12/30/2008
• Status: Active Grant

• Current Assignee: GE Infrastructure Technology, LLC (GE Vernova, Inc.)
• Original Assignee: General Electric Company
• Inventors: Benjamin, Edward D., Snook, Daniel D.
• Primary Examiner(s): LEE, BENNY T
• Application Number:
  US12/346,278
• Publication Number:
  US 20100166564A1
• Time in Patent Office: 1,309 Days
• Field of Search: 416/96.A, 416/97.R, 415/115
• US Class Current: 415/115
• CPC Class Codes: F01D 5/188 with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
• CPC Class Codes: F01D 5/189 the insert having a tubular cross-section, e.g. airfoil shape
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A turbine blade with a generally hollow airfoil having an outer wall that defines a chamber for receiving cooling air, the airfoil comprising a leading edge that resides in an upstream direction, a trailing edge that resides in a downstream direction, a convex suction side, a concave pressure side, and an insert disposed within the chamber that is configured to initially receive at least a portion of the cooling air entering the chamber and direct the cooling air through a plurality of insert apertures to cool the inner surface of the outer wall, the insert further comprising a configuration that generally conforms to the contour of the outer wall of the chamber but in spaced relation thereto, wherein the chamber and insert narrow as they extend toward the trailing edge, the insert eventually terminating and the chamber eventually terminating at a pin array section, wherein a first distance exists that comprises the generally axial distance between the position of downstream termination point of the insert and the position of an upstream beginning point of the pin array section, wherein the pin array section, at a downstream end, comprises a plurality of openings that define an inlet to a plurality of trailing edge cooling apertures, and wherein the chamber, the insert, and the pin array section are configured such that the first distance is approximately minimized.

Claims

1. A turbine blade with a generally hollow airfoil having an outer wall that defines a chamber for receiving cooling air, the airfoil comprising a leading edge that resides in an upstream direction, a trailing edge that resides in a downstream direction, a convex suction side, a concave pressure side, and an insert disposed within the chamber that is configured to initially receive at least a portion of the cooling air entering the chamber and direct the cooling air through a plurality of insert apertures to cool the inner surface of the outer wall, the insert further comprising a configuration that generally conforms to the contour of the outer wall of the chamber but in spaced relation thereto, wherein a portion of the cooling air exits the airfoil through a plurality of film cooling apertures formed through the outer wall, wherein the chamber and insert narrow as they extend toward the trailing edge, the insert eventually terminating and the chamber eventually terminating at a pin array section, which includes a passageway in which a plurality of cooling pins extend transversely across and are integral to the opposed walls that define the pin array section, wherein a first distance exists that comprises the generally axial distance between the position of downstream termination point of the insert and the position of an upstream beginning point of the pin array section, wherein the pin array section, at a downstream end, comprises a plurality of openings that define an inlet to a plurality of trailing edge cooling apertures that extend from the pin array section to the trailing edge of the airfoil where an outlet is provided through which a portion of the cooling air may exit the airfoil, and wherein the chamber, the insert, and the pin array section are configured such that the first distance is approximately minimized;

wherein the configuration of the chamber, the insert, and the pin array section that approximately minimizes the first distance includes a contoured exit that makes a smooth transition from the broader diameter of the chamber to the narrow diameter of the pin array section.

2. The turbine blade of claim 1, wherein the turbine blade comprises a rotor blade.

3. The turbine blade of claim 1, wherein the smooth transition of the contoured exit comprises a smooth rapid transition from the broader diameter of the chamber to the narrow diameter of the pin array section.

4. The turbine blade of claim 1, wherein the shape of the contoured exit, as described moving downstream, comprises a concave curve that transitions to a convex curve that narrows the contoured exit rapidly.

5. The turbine blade of claim 1, wherein the pins of the pin array section are configured in a plurality of rows.

6. The turbine blade of claim 1, wherein the chamber comprises a leading edge chamber and a trailing edge chamber that are separated by a partition.

7. The turbine blade of claim 1, wherein all of the film cooling apertures through the outer wall comprise a location upstream of a throat, the throat comprising the minimum flow area between the airfoils of the turbine blade and an airfoil of a neighboring turbine blade once the turbine blade is installed.

8. The turbine blade of claim 1, wherein the configuration of the chamber, the insert, and the pin array section that approximately minimizes the first distance includes the trailing edge of the insert being configured such that the insert extends toward the trailing edge a maximum distance while just maintaining a shape that is insertable into the airfoil during assembly.

9. The turbine blade of claim 1, wherein the configuration of the chamber, the insert, and the pin array section that approximately minimizes the first distance includes the trailing edge of the insert being configured such that the insert extends toward the trailing edge a maximum distance given a minimum curvature of the insert, a minimum wall thickness of the outer wall, and a minimum trailing edge passage thickness.

10. The turbine blade of claim 9, wherein the minimum curvature of the insert comprises a minimum curvature that may be formed in the insert given material limitations and a desired level of durability.

11. The turbine blade of claim 10, wherein the minimum curvature of the insert comprises approximately a radius that is equal to twice the wall thickness of the insert.

12. The turbine blade of claim 9, wherein the minimum outer wall thickness comprises a minimum outer wall thickness that may be formed given material and casting limitations and a desired level of outer wall durability.

13. The turbine blade of claim 9, wherein the minimum trailing edge passage thickness comprises a minimum clearance between the insert and the outer wall along the trailing edge of the chamber given a desired level of flow of cooling air therethrough.

14. The turbine blade of claim 1, wherein the configuration of the chamber, the insert, and the pin array section that approximately minimizes the first distance includes the upstream beginning point of the pin array section extending approximately as far upstream as a maximum pin length allows.

15. The turbine blade of claim 14, wherein the maximum pin length comprises the maximum length of the pins given a desired level of heat transfer through the pin array section and the casting capabilities given the pin diameter that corresponds to that desired level of heat transfer through the pin array section.

16. The turbine blade of claim 1, wherein the turbine blade comprises a stator blade.

17. The turbine blade of claim 16, wherein the turbine blade configured to operate in a 7FA+e turbine engine manufactured by The General Electric Company of Schenectady, N.Y.

18. The turbine blade of claim 1, wherein the turbine blade is configured to operate as a stage one stator blade.