Air cooled turbine airfoil with sequential impingement cooling

• US 8,167,537 B1
• Filed: 11/17/2011
• Issued: 05/01/2012
• Est. Priority Date: 01/09/2009
• 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: Plank, William L., Downs, James P., Fedock, John A.
• Primary Examiner(s): ZARNEKE, DAVID A
• Application Number:
  US13/298,379
• Time in Patent Office: 166 Days
• Field of Search: 415/115, 416/97.R
• US Class Current: 415/115
• CPC Class Codes: F01D 5/147 Construction, i.e. structural features, e.g. of weight-saving hollow blades F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18
• CPC Class Codes: F01D 5/186 Film cooling F01D5/187 takes precedence
• CPC Class Codes: F01D 5/187 Convection cooling
• 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: F05D 2260/201 by impingement of a fluid
• CPC Class Codes: F05D 2260/202 by film cooling
• CPC Class Codes: F05D 2260/221 Improvement of heat transfer
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

An air cooled turbine airfoil such as a stator vane in which the airfoil is hollowed out and an insert is secured within the hollowed out section that produces sequential impingement cooling of the airfoil. The insert is formed from a plurality of plates bonded together outside of or inside of the airfoil to form a single piece insert with the cooling circuit. The plates are bonded together using TLP bonding process with sheets of boron placed between adjacent plates so that no excess material seeps out and into the cooling features formed with the plates. The cooling features of the plates are formed by photo-etching.

Claims

1. A method of forming a sequential impingement cooling insert for a turbine airfoil comprising the steps of:

forming a plurality of sheets having an airfoil shape;

photo-etching the plurality of sheets to form plates that form a sequential impingement cooling circuit;

placing Boron between adjacent plates;

compressing the plates together with the plates in position for bonding; and

,

securing the plates together using a transient liquid phase bonding process.

2. The method of forming a sequential impingement cooling insert of claim 1, and further comprising:

forming the sheets from IN625 sheet metal.

3. The method of forming a sequential impingement cooling insert of claim 1, and further comprising the step of:

forming the insert from an alternating formation of an upper plate and a lower plate that together form the sequential impingement cooling circuit that provides impingement cooling to a backside surface of the airfoil walls.

4. The method of forming a sequential impingement cooling insert of claim 1, and further comprising the step of:

the Boron is a sheet of Boron with a thickness of about 0.0002 inches.

5. The method of forming a sequential impingement cooling insert of claim 3, and further comprising the step of:

forming the plates with a plurality of insert securing members that also form seals to separate adjacent impingement cavities.

6. The method of forming a sequential impingement cooling insert of claim 1, and further comprising the steps of:

forming the insert from a series of upper and lower plates with the upper plates having a first row of impingement cooling holes in a forward pressure side section of the airfoil, a third row of impingement cooling holes in a forward suction side section of the airfoil, and a fourth row of impingement cooling holes in an aft suction side section of the airfoil; and

,

forming the lower plates with a second row of impingement cooling holes in an aft pressure side section of the airfoil and a forward pressure side collection channel connected to the second row of impingement holes.

7. The method of forming a sequential impingement cooling insert of claim 1, and further comprising the steps of:

forming the plates with a cooling air supply channel in a forward section of each plate that also forms a passage to align the plates in position for bonding.

8. A method of forming an air cooled turbine airfoil having impingement cooling of the airfoil walls, the method comprising the steps of:

forming an airfoil with a hollow inner section such that the airfoil walls can be cooled using impingement cooling air;

forming a plurality of inserting securing members on the hollow inner section of the airfoil;

forming an insert from a plurality of plates that are bonded together to form a sequential impingement cooling circuit to produce impingement cooling on a forward section and an aft section of a pressure side wall and a suction side wall of the airfoil;

securing the insert inside the hollow inner section of the airfoil.

9. The method of forming an air cooled turbine airfoil of claim 8, and further comprising the steps of:

obtaining an old airfoil; and

,

hollowing out the old airfoil by removing an existing internal cooling air circuit from the airfoil.

10. The method of forming an air cooled turbine airfoil of claim 8, and further comprising the steps of:

forming the insert from a plurality of plates made from IN625; and

,

bonding the inserts together with a sheet of boron between adjacent plates using a transient liquid phase bonding process.

11. The method of forming an air cooled turbine airfoil of claim 8, and further comprising the steps of:

photo-etching a sequential impingement cooling circuit within the plates prior to bonding the plates together.

12. A method of forming a highly twisted air cooled turbine airfoil having impingement cooling of the airfoil walls, the method comprising the steps of:

forming a highly twisted airfoil with a hollow inner section such that the airfoil walls can be cooled using impingement cooling air;

forming a plurality of alternating plates having an airfoil shape that forms a sequential impingement cooling circuit for the airfoil walls when bonded together;

placing the plurality of plates within the hollow inner section of the airfoil with a bonding agent between adjacent plates; and

,

bonding the plurality of plates to form a single piece insert while the plates are inside the airfoil hollow inner section.

13. The method of forming a highly twisted air cooled turbine airfoil of claim 12, and further comprising the step of:

compressing the plurality of plates together prior to the bonding process.

14. The method of forming a highly twisted air cooled turbine airfoil of claim 12, and further comprising the step of:

forming the plates from IN625.

15. The method of forming a highly twisted air cooled turbine airfoil of claim 12, and further comprising the step of:

using Boron as the bonding agent.

16. The method of forming a highly twisted air cooled turbine airfoil of claim 12, and further comprising the steps of:

bonding several small stacks of plates together outside of the airfoil;

placing the small stack of bonded plates inside the hollow inner section of the airfoil with a bonding agent between adjacent small stacks of bonded plates; and

,

bonding the small stacks of bonded plates together to form a single piece insert.

17. The method of forming a highly twisted air cooled turbine airfoil of claim 12, and further comprising the steps of:

compressing the small stacks of bonded inserts together prior to bonding.

18. A plate used to form an insert that provides sequential impingement cooling for a backside surface of a turbine airfoil, the plate comprising;

the plate has an airfoil shape with a leading edge region and a trailing edge region with a pressure side surface and a suction side surface extending between the edges;

three insert retaining and seal forming members located on the pressure side surface and the suction side surface and the leading edge region of the plate;

a first row of impingement cooling holes located along a forward section on the pressure side surface of the plate;

a second row of impingement cooling holes located along a forward section on the suction side surface of the plate;

a third row of impingement cooling holes located along an aft section on the suction side surface of the plate;

a cooling air supply channel located in a forward section of the plate and connected to the first row of impingement cooling holes;

a first cooling air passage located in the aft section on the pressure side surface of the plate and connected to the second row of impingement cooling holes; and

,

a second cooling air passage located in the aft section on the pressure side surface of the plate and connected to the third row of impingement cooling holes.

19. The plate of claim 18, and further comprising:

a plate alignment hole formed within the plate.

20. The plate of claim 18, and further comprising:

the plate is formed from a thin sheet of IN625.

21. The plate of claim 18, and further comprising:

the impingement cooling holes are photo-etched into the plate.