Cooled turbine stator vane

• US 7,921,654 B1
• Filed: 09/07/2007
• Issued: 04/12/2011
• Est. Priority Date: 09/07/2007
• Status: Expired due to Fees

• Current Assignee: Florida Turbine Technologies, Inc. (Kratos Defense & Security Solutions Incorporated)
• Original Assignee: Florida Turbine Technologies, Inc. (Kratos Defense & Security Solutions Incorporated)
• Inventors: Liang, George
• Primary Examiner(s): Cuff; Michael
• Assistant Examiner(s): Wongwian; Phutthiwat
• Application Number:
  US11/900,034
• Time in Patent Office: 1,313 Days
• Field of Search: 608/06, 415/115, 415/116, 416/92, 416/95, 416/96.A, 416/96.R, 416/97.A, 416/97.R
• US Class Current: 60/806
• CPC Class Codes: F01D 5/186 Film cooling F01D5/187 takes precedence
• CPC Class Codes: F01D 9/041 using blades F01D5/148 takes precedence
• CPC Class Codes: F05B 2240/801 cooled platforms
• CPC Class Codes: F05D 2240/81 Cooled platforms
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A first stage turbine stator vane used in an industrial gas turbine engine, the vane having an outer endwall and an inner endwall with the airfoil extending between the two endwalls. A showerhead arrangement of film cooling holes is located along the leading edge region, and a row of exit cooling air slots is located along the trailing edge of the airfoil. A slanted rib extends from the outer endwall to the inner endwall and separates the vane into a forward cavity and an aft cavity. A leading edge impingement tube is secured within the forward cavity to provide impingement cooling to the leading edge walls of the airfoil. The leading edge impingement tube includes a cooling air inlet section extending out from the inner endwall so that a vena contractor forms in the tube entrance before the impingement holes begin. The leading edge impingement tube narrows in the cooling air flow direction. The trailing edge impingement tube has similar construction but has the cooling air inlet extending out from the outer endwall. With this design, the first stage vane can use both impingement cooling of the leading edge region and showerhead film cooling of the leading edge airfoil surface to allow for a higher gas flow temperature across the vane.

Claims

1. A turbine stator vane for use in a gas turbine engine, the vane comprising:

an inner diameter endwall and an outer diameter endwall;

an airfoil extending between the inner and the outer diameter endwalls;

a showerhead arrangement includes film cooling holes in a lower half of a leading edge oriented to direct cooling air upward, and film cooling holes in an upper half of the leading edge oriented to direct cooling air downward;

a row of exit cooling slots on the trailing edge region of the airfoil;

a slanted rib slants toward the trailing edge from the outer endwall to the inner endwall, the slanted rib extending between the outer diameter endwall and the inner diameter endwall and separating a leading edge cavity within the airfoil from a trailing edge cavity;

a leading edge impingement tube secured within the leading edge cavity;

a trailing edge impingement tube secured within the trailing edge cavity;

the row of exit cooling slots being connected directly to the trailing edge cavity; and

,

cooling air supply means to supply compressed cooling air to the leading edge cavity and the trailing edge cavity.

2. The turbine stator vane of claim 1, and further comprising:

the leading edge impingement tube includes an opening on the inner diameter endwall side of the airfoil, and the tube narrows in the direction of cooling air flow within the tube.

3. The turbine stator vane of claim 2, and further comprising:

the trailing edge impingement tube includes an opening that extends out from the inner diameter endwall to form an entrance space in which a vena contractor can form and end before the impingement holes in the tube.

4. The turbine stator vane of claim 1, and further comprising:

the trailing edge impingement tube includes an opening on the outer diameter endwall side of the airfoil, and the tube narrows in the direction of cooling air flow within the tube.

5. The turbine stator vane of claim 1, and further comprising:

the leading edge impingement tube and the trailing edge impingement tube are sized to fit within the two cavities to produce impingement cooling of the inner airfoil walls opposed to the tubes.

6. The turbine stator vane of claim 1, and further comprising:

an outer diameter endwall impingement plate secured to the outer diameter endwall and forming an outer endwall impingement cavity on the pressure side and the suction side of the endwall;

impingement holes in the outer diameter endwall impingement plate; and

,

film cooling holes on the outer diameter endwall to direct film cooling air from the outer endwall impingement cavity into the hot gas flow.

7. The turbine stator vane of claim 6, and further comprising:

an inner diameter endwall impingement plate secured to the inner diameter endwall and forming an inner endwall impingement cavity on the pressure side and the suction side of the endwall;

impingement holes in the inner diameter endwall impingement plate; and

, film cooling holes on the inner diameter endwall to direct film cooling air from the inner endwall impingement cavity into the hot gas flow.

8. The turbine stator vane of claim 2, and further comprising:

the leading edge cavity impingement tube includes two stand-offs located near the outer endwall and the inner endwall to support the tube within the cavity.

9. A turbine stator vane for use in a gas turbine engine, the vane comprising:

an inner diameter endwall and an outer diameter endwall;

an airfoil extending between the inner and the outer diameter endwalls;

a showerhead arrangement of film cooling holes on a leading edge region of the airfoil, the showerhead includes an upper section of film cooling holes directed downwards and a lower section of film cooling holes directed upwards;

a row of exit cooling slots on the trailing edge region of the airfoil;

a slanted rib slants toward the trailing edge from the outer endwall to the inner endwall, the slanted rib extending between the outer diameter endwall and the inner diameter endwall and separating a leading edge cavity within the airfoil from a trailing edge cavity;

a leading edge impingement tube secured within the leading edge cavity;

a trailing edge impingement tube secured within the trailing edge cavity;

the row of exit cooling slots being connected directly to the trailing edge cavity; and

,

cooling air supply means to supply compressed cooling air to the leading edge cavity and the trailing edge cavity.

10. The turbine stator vane of claim 9, and further comprising:

the leading edge impingement tube projects out from the vane endwall at a distance X such that a vena contractor is fully reattached to the tube upstream of the impingement holes.

11. The turbine stator vane of claim 10, and further comprising:

the distance X is at least seven times the difference between the tube diameter and the minimum diameter of the vena contractor formed within the tube inlet.

12. The turbine stator vane of claim 10, and further comprising:

the trailing edge impingement tube projects out from the vane endwall at a long enough distance X such that a vena contractor forms within the tube inlet will end before the hot section of the airfoil begins.

13. The turbine stator vane of claim 9, and further comprising:

the impingement cooling holes on the impingement tube and the showerhead cooling holes on the leading edge are sized such that the pressure drop across the impingement holes is less than 30% of the total pressure drop across both the impingement and the showerhead cooling holes.

14. A turbine stator vane for use in a gas turbine engine, the vane comprising:

an inner diameter endwall and an outer diameter endwall;

an airfoil extending from the inner diameter endwall to the outer diameter endwall;

a leading edge cooling supply cavity with a showerhead arrangement of film cooling holes on a leading region of the airfoil;

a trailing edge cavity disposed within the airfoil and separating from the leading edge cavity;

an impingement tube sized to fit within the leading cavity, the impingement tube having impingement cooling holes to direct impingement cooling air to a leading edge region of the cavity; and

,

the impingement tube includes an inlet projection out from an inner impingement plate that connected to the inner diameter endwall at a distance X such that a vena contractor is fully reattached to the tube upstream from the impingement holes.

15. The turbine stator vane of claim 14, and further comprising:

the distance X is at least seven times the difference between the tube diameter and the minimum diameter of the vena contractor formed within the tube inlet.

16. The turbine stator vane of claim 14, and further comprising:

the impingement tube narrows in the direction of the cooling air flow within the tube such that the cooling air pressure within the tube is substantially constant.

17. The turbine stator vane of claim 14, and further comprising:

the impingement cooling holes on the impingement tube and the showerhead cooling holes on the leading edge are sized such that the pressure drop across the impingement holes is less than 30% of the total pressure drop across both the impingement and the showerhead cooling holes.