Air cooled turbine airfoil

• US 8,043,057 B1
• Filed: 12/21/2007
• Issued: 10/25/2011
• Est. Priority Date: 12/21/2007
• 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): Look; Edward
• Assistant Examiner(s): White; Dwayne J
• Application Number:
  US12/004,961
• Time in Patent Office: 1,404 Days
• Field of Search: 415/115, 415/116, 416/96.R, 416/96.A, 416/97.R
• US Class Current: 416/97.00R
• 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: F01D 9/041 using blades F01D5/148 takes precedence
• CPC Class Codes: F05D 2260/201 by impingement of a fluid

Abstract

A turbine airfoil with a multiple impingement cooling circuit to provide backside impingement cooling of the leading edge region and the pressure and suction side walls. A leading edge cavity and a mid-chord cavity are separated by a rib. A first baffle is secured within the leading edge cavity and forms a series of impingement compartments and impingement cooling holes to channel cooling air along the first baffle and provide impingement cooling along the backside wall of the leading edge region. A second baffle is secured within the mid-chord cavity and forms a series of pressure side and suction side impingement compartments and impingement cooling holes alternating from the pressure side wall to the suction side wall to channel cooling air along the second baffle and provide impingement cooling along the backside walls of the pressure and suction sides. A spent air collection channel extends along the trailing edge region and is connected to a row of exit cooling holes along the trailing edge of the airfoil. Cooling air from the first baffle flows into the second baffle, and from the second baffle into the spend air collection channel and out through the exit cooling holes.

Claims

1. An air cooled turbine airfoil comprising:

a leading edge and a trailing edge;

a pressure side wall and a suction side wall;

a leading edge cavity formed in the leading edge region of the airfoil;

a mid-chord cavity located aft separated from the leading edge cavity by a rib; and

,

a first baffle secured within the leading edge cavity, the first baffle forming a series of impingement compartments such that cooling air flows from one compartment to the next compartment, adjacent compartments being connected by a plurality of impingement holes and a spent air return hole.

2. The air cooled turbine airfoil of claim 1, and further comprising;

the a spent air channel associated with each impingement compartment and connected thereto through associated impingement holes, the spent air channel being formed by the leading edge wall, and adjacent spend air channels being separated by a stand-off.

3. The air cooled turbine airfoil of claim 1, and further comprising;

a second baffle secured within the mid-chord cavity, the second baffle forming a series of pressure side wall impingement compartment and suction side wall impingement compartments, the pressure side wall compartments alternating between the suction side wall compartments.

4. The air cooled turbine airfoil of claim 3, and further comprising;

the pressure side wall compartments are separated from the suction side wall compartments by slanted floors.

5. The air cooled turbine airfoil of claim 4, and further comprising;

pressure side impingement holes in the pressure side wall compartments; and

,

suction side impingement holes in the suction side wall compartments.

6. The air cooled turbine airfoil of claim 5, and further comprising;

the slanted floors allow for some of the pressure side impingement holes to be spanwise aligned with some of the suction side impingement holes in adjacent compartments.

7. The air cooled turbine airfoil of claim 3, and further comprising;

cooling air connection means to connect the cooling air outlet from the first baffle to the inlet of the second baffle.

8. The air cooled turbine airfoil of claim 3, and further comprising;

each of the pressure side wall and suction side wall compartments located inside of the end compartments includes a spend air return hole to supply cooling air into the compartment and a plurality of impingement holes to discharge cooling air from the compartment.

9. The air cooled turbine airfoil of claim 3, and further comprising;

spent air channels formed along the pressure side wall and the suction side wall, adjacent spent air channels being separated by a stand-off.

10. The air cooled turbine airfoil of claim 9, and further comprising;

the last spend air channel in the series flow connected to a spent air collection channel located in the trailing edge region of the airfoil; and

,

a row of trailing edge exit holes connecting the spent air collection channel.

11. A process for cooling an airfoil used in a gas turbine engine, the process comprising the steps of:

supplying pressurized cooling air to a first leading edge impingement compartment;

impinging cooling air onto a first surface of the leading edge wall;

collecting the first impinging cooling air into a second impingement compartment;

impinging the cooling air from the second impingement compartment onto a second surface of the leading edge wall different from the first surface;

collecting the second impinging air into a last impingement compartment; and

,

impinging the cooling air from the last compartment onto a last surface of the leading edge wall different from the first and the second surfaces.

12. The process for cooling an airfoil of claim 11, and further including the steps of:

collecting the last compartment impinging air into a first mid-chord impinging compartment;

impinging cooling air onto a first surface of the pressure side wall of the airfoil;

collecting the impinging cooling air into a second mid-chord impinging compartment; and

,

impinging cooling air onto a first surface of the suction side wall of the airfoil.

13. The process for cooling an airfoil of claim 12, and further including the steps of:

collecting the first suction side wall impinging cooling air into a third mid-chord impinging compartment; and

,

impinging cooling air onto a second surface of the pressure side wall.

14. The process for cooling an airfoil of claim 13, and further including the steps of:

collecting the first surface of the pressure side wall impinging cooling air into a fourth mid-chord impinging compartment; and

,

impinging cooling air onto a second surface of the suction side wall.

15. An air cooled turbine airfoil comprising:

a leading edge and a trailing edge;

a pressure side wall and a suction side wall;

a leading edge cavity extending along the spanwise length of the airfoil;

a mid-chord cavity extending along the spanwise length of the airfoil;

the leading edge cavity and the mid-chord cavity separated by a rib;

a leading edge impingement baffle secured within the leading edge cavity, the leading edge impingement baffle forming a series of impingement compartments and impingement holes to channel cooling air along the airfoil and provide impingement cooling along the leading edge wall of the airfoil;

a mid-chord impingement baffle secured within the mid-chord cavity, the mid-chord impingement baffle forming a series of pressure side and suction side impingement compartments and impingement holes to channel cooling air along the airfoil and provide impingement cooling along the pressure side and the suction side walls of the airfoil; and

,

means to channel the cooling air from the outlet of the leading edge baffle to the inlet of the mid-chord baffle.

16. The air cooled turbine airfoil of claim 15, and further comprising:

a spent air collection channel aft of the mid-chord cavity and in the trailing edge region of the airfoil;

a row of exit cooling holes along the trailing edge of the airfoil and connected to the spent air collection channel; and

,

means to channel the cooling air from the outlet of the mid-chord baffle to the inlet of the spent air collection channel.

17. The air cooled turbine airfoil of claim 16, and further comprising:

the airfoil has no film cooling holes and all of the cooling air supplied to the leading edge baffle is eventually discharged through the exit cooling holes along the trailing edge of the airfoil.