Two piece hollow turbine blade with serpentine cooling circuits

• US 7,862,299 B1
• Filed: 03/21/2007
• Issued: 01/04/2011
• Est. Priority Date: 03/21/2007
• 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): Eastman; Aaron R
• Application Number:
  US11/726,334
• Time in Patent Office: 1,385 Days
• Field of Search: 416/97.R, 415/115
• US Class Current: 416/97.00R
• 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 5/187 Convection cooling
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A turbine blade for use in a gas turbine engine, the blade being formed from two pieces bonded together along the blade chamber line to from a pressure side piece and a suction side piece. The pressure side piece includes a first serpentine flow cooling circuit with a first leg located on the suction side leading edge region and the second leg on the pressure side leading edge region with the last leg adjacent to the trailing edge region and connected to exit slots to discharge cooling air out the pressure side of the trailing edge. The suction side piece includes a second serpentine flow cooling circuit with a first leg adjacent to the trailing edge region and connected to suction side exit slots to discharge cooling air. The suction side serpentine circuit ends in a last leg adjacent to the first leg of the pressure side serpentine circuit with a row of film cooling holes to discharge cooling air from the last leg to the suction side airfoil surface for film cooling. The two serpentine flow circuits are separated from each other so that the cooling design can be flexible.

Claims

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

an airfoil pressure side piece extending from the root to the tip of the blade and having a first serpentine flow cooling circuit therein;

an airfoil suction side piece extending from the root to the tip of the blade and having a second serpentine flow cooling circuit therein;

a bond formed between the two pieces to form a single turbine airfoil;

a first row of pressure side exit holes on the trailing edge of the blade in fluid communication with the first serpentine flow cooling circuit; and

,

a second row of suction side exit holes on the trailing edge of the blade in fluid communication with the second serpentine flow cooling circuit.

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

the first row of pressure side exit holes and the second row of pressure side exit holes are each connected to the respective serpentine flow circuit through a row of metering holes and at least one row of pin fins to promote the heat transfer effect to the cooling air.

3. A turbine airfoil for use in a gas turbine engine, the airfoil comprising:

an airfoil pressure side piece extending from the root to the tip of the blade and having most of a first serpentine flow cooling circuit therein;

an airfoil suction side piece extending from the root to the tip of the blade and having a second serpentine flow cooling circuit therein;

a bond formed between the two pieces to form a single turbine airfoil; and

the first serpentine flow cooling circuit includes a first leg on the suction side of the leading edge region of the airfoil, and a second leg on the pressure side of the leading edge region of the airfoil.

4. The turbine airfoil of claim 3, and further comprising:

the second serpentine flow cooling circuit includes a first leg adjacent to the trailing edge region of the airfoil and a last leg adjacent to the first leg of the first serpentine flow cooling circuit.

5. The turbine airfoil of claim 4, and further comprising:

the last leg of the second serpentine flow cooling circuit includes a row of film cooling holes to discharge film cooling air to the suction side surface of the airfoil.

6. The turbine airfoil of claim 4, and further comprising:

the first and second serpentine flow circuits are both five pass serpentine flow circuits.

7. A turbine airfoil for use in a gas turbine engine, the airfoil comprising:

an airfoil pressure side piece extending from the root to the tip of the blade and having a most of a first serpentine flow cooling circuit therein;

an airfoil suction side piece extending from the root to the tip of the blade and having a second serpentine flow cooling circuit therein;

the first serpentine flow cooling circuit being an aft flowing cooling circuit;

the second serpentine flow cooling circuit being a forward flowing cooling circuit;

the first and second serpentine flow cooling circuits are formed as separate cooling circuits having respective inlets located in the root of the blade; and

,

a bond formed between the pressure side and suction side pieces to form a single turbine airfoil.

8. The turbine airfoil of claim 7, and further comprising:

the bond is formed between the two airfoil pieces at the airfoil chamber line.

9. The turbine airfoil of claim 7, and further comprising:

The first and second serpentine flow circuits are both five pass serpentine flow circuits.

10. The turbine airfoil of claim 7, and further comprising:

a first row of pressure side exit holes on the trailing edge of the blade in fluid communication with the first serpentine flow cooling circuit; and

,

a second row of suction side exit holes on the trailing edge of the blade in fluid communication with the second serpentine flow cooling circuit.

11. The turbine airfoil of claim 7, and further comprising:

the first serpentine flow cooling circuit includes a first leg on the suction side of the leading edge region of the airfoil and a second leg on the pressure side of the leading edge region of the airfoil.