Turbine airfoil formed as a single piece but with multiple materials

• US 8,162,609 B1
• Filed: 11/11/2011
• Issued: 04/24/2012
• Est. Priority Date: 12/18/2008
• 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): Zarneke, David
• Application Number:
  US13/294,219
• Time in Patent Office: 165 Days
• Field of Search: 416/96.R, 416/97.R, 416/241.B, 416/241.R
• US Class Current: 416/96.R
• CPC Class Codes: F01D 5/187 Convection cooling
• CPC Class Codes: F05D 2230/20 essentially without removing material
• CPC Class Codes: F05D 2230/30 with deposition of material
• CPC Class Codes: F05D 2250/314 the axes being inclined in relation to each other
• CPC Class Codes: F05D 2260/2212 by creating turbulence vortex generators, turbulators or the like for mixing F05D2240/127
• CPC Class Codes: F05D 2260/22141 using fins or ribs

Abstract

An air cooled turbine airfoil includes a multiple pass serpentine flow cooling circuit formed from a metallic printing process in which the blade can be printed from different materials as a single piece blade. The blade includes a multiple pass serpentine cooling circuit in which the channels include ribs and pin fins that are formed perpendicular to the airfoil wall. The inner chordwise extending rib, the ribs and the f[pin fins and the outer airfoil wall call all be printed as a single piece but all with a different material in order to control the metal temperature of the blade. a seven pass serpentine flow cooling circuit can be formed that flows along the pressure side wall and then the suction side wall and use low flow cooling amount.

Claims

1. An air cooled turbine airfoil comprising:

a leading edge and a trailing edge;

a pressure side wall and a suction side wall extending between the leading and trailing edges;

a multiple pass serpentine flow cooling circuit extending along a side wall of the airfoil;

a plurality of pin fins extending across each of the channels of the multiple pass serpentine flow cooling circuit; and

,

the pin fins are perpendicular to a surface of the airfoil wall.

6. The air cooled turbine airfoil of claim 1, and further comprising:

the outer airfoil wall has a thickness of around 0.020 inches.

7. The air cooled turbine airfoil of claim 1, and further comprising:

a TBC applied over the outer airfoil wall; and

,

the TBC is formed as a single piece with the outer airfoil wall from a metal printing process.

2. An air cooled turbine rotor blade comprising:

an airfoil with a leading edge region and a trailing edge region and a pressure side wall and a suction side wall both extending between the leading and trailing edge regions;

a multiple pass serpentine flow cooling circuit formed within the airfoil and extending along the pressure side wall and the suction side wall;

a TBC applied over the airfoil walls; and

,

the airfoil walls and the TBC being formed as a single piece from a metal printing process.

3. The air cooled turbine rotor blade of claim 2, and further comprising:

a plurality of pin fins extending across each of the channels of the multiple pass serpentine flow cooling circuit; and

,

the pin fins are perpendicular to a surface of the airfoil wall.

4. The air cooled turbine rotor blade of claim 2, and further comprising:

the multiple pass serpentine flow cooling circuit is a seven pass serpentine flow cooling circuit with a first leg located along the leading edge region, a fourth leg located in the trailing edge region, and a last leg located on the suction side wall adjacent to the leading edge region of the airfoil.

5. The air cooled turbine rotor blade of claim 4, and further comprising:

a first row of film cooling holes connected to the sixth leg of the serpentine flow cooling circuit; and

,

a second row of film cooling holes connected to the seventh leg of the serpentine flow cooling circuit.

8. An air cooled turbine rotor blade comprising:

an airfoil with a leading edge region and a trailing edge region, and a pressure side wall and a suction side wall extending between the leading and trailing edge regions;

a chordwise extending rib extending along a middle of the airfoil;

an outer airfoil wall;

a plurality of ribs and pin fins extending from the chordwise extending rib to the airfoil wall to from cooling air passages;

the chordwise extending rib and the airfoil wall and the plurality of ribs and pin fins being formed as a single piece; and

,

the chordwise extending rib and the airfoil wall and the plurality of ribs and pin fins being made from three different materials.

9. The air cooled turbine rotor blade of claim 8, and further comprising:

the outer airfoil wall has a thickness of around 0.020 inches.

10. The air cooled turbine rotor blade of claim 8, and further comprising:

a TBC applied over the outer airfoil wall; and

,

the TBC is formed as a single piece with the outer airfoil wall from a metal printing process.

11. The air cooled turbine rotor blade of claim 10, and further comprising:

the outer airfoil wall is formed from a metallic material; and

,

the TBC is formed from a ceramic material.