Turbine airfoil with metering plates for refresher holes

• US 6,491,496 B2
• Filed: 02/23/2001
• Issued: 12/10/2002
• Est. Priority Date: 02/23/2001
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Starkweather, John Howard
• Primary Examiner(s): Look, Edward K.
• Assistant Examiner(s): Nguyen, Ninh
• Application Number:
  US09/791,177
• Publication Number:
  US 20020119045A1
• Time in Patent Office: 655 Days
• Field of Search: 415/115, 415/116, 416/96.R, 416/97.R
• US Class Current: 416/97.00R
• CPC Class Codes: F01D 5/187 Convection cooling
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A gas turbine engine hollow airfoil has chordally spaced apart leading and trailing edges extending radially from a radially inner base to a radially outer airfoil tip. A cooling circuit within the airfoil has radially extending first, middle, and last channels arranged respectively in series with the first channel in fluid communication with a source of cooling air from outside the airfoil. The last channel is in fluid communication with one of the edges. A refresher passageway extends through a radially inner wall bounding a radially inner portion of the last channel and is in fluid communication with the source of cooling air. The refresher passageway is separate, spaced apart, and independent from the first channel. In one embodiment, a metering plate covers an inlet to the refresher passageway and the metering plate has a metering hole over the inlet and the metering hole is adjustable.

Claims

1. A gas turbine engine hollow airfoil comprising;

an airfoil outer wall having widthwise spaced apart pressure and suction side walls joined together at chordally spaced apart leading and trailing edges of said airfoil and extending radially from a radially inner base to a radially outer airfoil tip,

a cooling circuit within said airfoil said cooling circuit having radially extending first, middle, and last channels arranged respectively in series,

said first channel being in fluid communication with a source of cooling air from outside said airfoil,

said last channel being in fluid communication with one of said edges,

a refresher passageway extending through a radially inner wall bounding a radially inner portion of said last channel and in fluid communication with said source of cooling air,

said refresher passageway is separate, spaced apart, and independent from said first channel,

an edge cooling plenum located between said last channel and said one of said edges and cooling air discharge apertures disposed through a radially extending rib between said last channel and said edge cooling plenum, and

wherein said edge cooling plenum is a leading edge cooling plenum and said cooling air discharge apertures are impingement cooling holes.

2. An airfoil as claimed in claim 1 further comprising leading edge cooling holes leading out of said edge cooling plenum through said outer wall around said leading edge.

3. A gas turbine engine hollow airfoil comprising:

an airfoil outer wall having widthwise spaced apart pressure and suction side walls joined together at chordally spaced apart leading and trailing edges of said airfoil and extending radially from a radially inner base to a radially outer airfoil tip,

a cooling circuit within said airfoil said cooling circuit having radially extending first, middle, and last channels arranged respectively in series,

said first channel being in fluid communication with a source of cooling air from outside said airfoil,

said last channel being in fluid communication with one of said edges,

a refresher passageway extending through a radially inner wall bounding a radially inner portion of said last channel and in fluid communication with said source of cooling air,

said refresher passageway is separate, spaced apart, and independent from said first channel, and

a metering plate covering an inlet to said refresher, passageway said metering plate having a metering hole over said inlet.

4. An airfoil as claimed in claim 3 wherein said metering hole is adjustable.

5. A gas turbine engine blade comprising:

a hollow airfoil extending radially outwardly from a root;

said airfoil comprising an airfoil outer wall having widthwise spaced apart pressure and suction side walls joined together at chordally spaced apart leading and trailing edges of said airfoil and extending radially from a radially inner base at said root to a radially outer airfoil tip,

a cooling circuit within said airfoil,

said cooling circuit having radially extending first, middle, and last channels arranged respectively in series,

said first channel extending through said root and having an entrance at a bottom surface of said root,

said last channel being in fluid communication with one of said edges,

a refresher passageway extending through a radially inner wall bounding a radially inner portion of said last channel and through said root,

said refresher passageway having an inlet at said bottom surface of said root, said inlet being separate and spaced apart from said entrance, an edge cooling plenum located between said last channel and said one of said edges and cooling air discharge apertures disposed through a radially extending rib between said last channel and said edge cooling plenum, and

wherein said edge cooling plenum is a leading edge cooling plenum and said cooling air discharge apertures are impingement cooling holes.

6. A blade as claimed in claim 5 further comprising leading edge cooling holes leading out of said edge cooling plenum through said outer wall around said leading edge.

7. A gas turbine engine blade comprising:

a hollow airfoil extending radially outwardly from a root;

said airfoil comprising an airfoil outer wall having widthwise spaced apart pressure and suction side walls joined together at chordally spaced apart leading and trailing edges of said airfoil and extending radially from a radially inner base at said root to a radially outer airfoil tip,

a cooling circuit within said airfoil,

said cooling circuit having radially extending first, middle, and last channels arranged respectively in series,

said first channel extending through said root and having an entrance at a bottom surface of said root,

said last channel being in fluid communication with one of said edges,

a refresher passageway extending through a radially inner wall bounding a radially inner portion of said last channel and through said root,

said refresher passageway having an inlet at said bottom surface of said root, said inlet being separate and spaced apart from said entrance, and

a metering plate on said bottom surface of said root, said metering plate covering said inlet to said refresher passageway, and said metering plate having a metering hole over said inlet.

8. A blade as claimed in claim 7 wherein said metering hole is adjustable.

9. A gas turbine engine blade comprising:

a hollow airfoil extending radially outwardly from a root;

said airfoil comprising an airfoil outer wall having widthwise spaced apart pressure and suction side walls joined together at chordally spaced apart leading and trailing edges of said airfoil and extending radially from a radially inner base at said root to a radially outer airfoil tip,

a forward flowing serpentine cooling circuit and an aft flowing serpentine cooling circuit within said airfoil,

said cooling circuits each having radially extending first, middle, and last channels arranged respectively in series,

each of said first channels extending through said root and having an entrance at a bottom surface of said root,

said last channel of said forward flowing serpentine cooling circuit in fluid communication with said leading edge,

said last channel of said aft flowing serpentine cooling circuit in fluid communication with said trailing edge,

forward and aft refresher passageways extending through forward and aft radially inner walls bounding radially inner portions of said forward and aft last channels, respectively, and through said root, and

said refresher passageways having inlets at said bottom surface of said root, said inlets being separate and spaced apart from said entrances.

10. A blade as claimed in claim 9 further comprising a leading edge cooling plenum located between said last channel of said forward flowing serpentine cooling circuit and impingement cooling holes disposed through a radially extending rib between said last channel of said forward flowing serpentine cooling circuit and said leading edge cooling plenum.

11. A blade as claimed in claim 10 further comprising leading edge cooling holes leading out of said leading edge cooling plenum through said outer wall around said leading edge.

12. A blade as claimed in claim 11 wherein said last channel is bounded by said trailing edge of said aft flowing serpentine cooling circuit.

13. A blade as claimed in claim 12 further comprising cooling air discharge apertures disposed through said trailing edge.

14. A blade as claimed in claim 13 wherein said cooling air discharge apertures are trailing edge cooling slots.

15. A blade as claimed in claim 14 furtherer comprising metering plates on said bottom surface of said root, said metering plates covering said inlets to said refresher passageways, and said metering plates having metering holes over said inlets.

16. A blade as claimed in claim 15 wherein said metering holes is adjustable.

17. A blade as claimed in claim 9 furtherer comprising metering plates on said bottom surface of said root, said metering plates covering said inlets to said refresher passageways, and said metering plates having metering holes over said inlets.

18. A blade as claimed in claim 17 wherein said metering holes is adjustable.