Turbine rotor blade with a nested parallel serpentine flow cooling circuit

• US 7,645,122 B1
• Filed: 12/01/2006
• Issued: 01/12/2010
• Est. Priority Date: 12/01/2006
• 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): Ellis; Ryan H
• Application Number:
  US11/607,587
• Time in Patent Office: 1,138 Days
• Field of Search: 415/115, 416/92, 416/96.R, 416/97.R
• US Class Current: 416/97.00R
• CPC Class Codes: F01D 5/187 Convection cooling
• CPC Class Codes: F05D 2240/307 related to the tip of a rotor blade
• CPC Class Codes: F05D 2250/185 serpentine-like
• CPC Class Codes: F05D 2250/70 Shape
• CPC Class Codes: F05D 2260/20 Heat transfer, e.g. cooling
• 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

A turbine airfoil used in a gas turbine engine, the airfoil including an internal cooling air circuit that includes two nested and parallel serpentine flow circuits that both flow in the airfoil aft direction. The first and second legs of the two nested serpentine circuits are separated by ribs so that the cooling air flows do not mix. The last leg of the two nested serpentine circuits is separated by a rib which includes a plurality of cross-over holes so that the flows can mix. The aft-most serpentine flow circuit of the two nested circuits includes a last leg that is connected to cooling slots spaced along the trailing edge of the airfoil such that cooling air from the last leg flows out the ducts. The forward-most serpentine circuit of the two nested circuits includes a blade tip channel extending along the blade tip and connecting the first leg with the second leg, the blade tip channel including a plurality of blade tip cooling holes. A leading edge cooling supply channel is connected to at least one impingement cavity by leading edge impingement holes to provide cooling to the leading edge region. The leading edge cooling supply channel is separated from the forward-most serpentine flow circuit by a rib such that the flows do not mix.

Claims

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

a root portion;

an airfoil portion extending from the root portion;

a blade tip portion;

a leading edge cooling supply channel;

an impingement cavity adjacent to the leading edge of the blade and in fluid communication with the leading edge supply channel by a plurality of impingement holes;

a first triple-pass serpentine flow cooling circuit having a first leg adjacent to the leading edge cooling supply cavity and separated from the supply channel by a continuous rib;

a second triple-pass serpentine flow cooling circuit nested within the first triple-pass serpentine flow cooling circuit, the two nested serpentine flow cooling circuits being separated by a continuous rib extending along the legs of the serpentine flow circuit;

a plurality of cooling slots arranged along the trailing edge of the blade, the slots being in fluid communication with the last leg of the second triple-pass serpentine flow circuit; and

,

blade tip cooling holes in fluid communication with the leading edge cooling channel, the first triple-pass serpentine flow circuit, and the last legs of the two nested serpentine flow circuits to provide cooling to the blade tip portion.

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

the continuous rib extending along the first and second legs of the two nested serpentine flow circuits does not allow the cooling air flow to mix; and

,

the continuous rib extending along the last leg of the serpentine flow circuit includes a plurality of cross-over holes to allow the cooling air flow to mix.

3. The turbine rotor blade of claim 1, and further comprising:

the leading edge cooling supply channel and the two nested serpentine flow circuits are formed by channels that extend between the pressure side wall and the suction side wall of the blade; and

,

the channels include trip strips to promote turbulent flow within the cooling air flow through the channels.

4. The turbine rotor blade of claim 1, and further comprising:

the nested triple-pass serpentine flow circuits extend substantially along the entire airfoil portion of the blade.

5. The turbine rotor blade of claim 1, and further comprising:

the leading edge cooling supply channel and the first legs of the two nested serpentine flow circuits each include a row of film cooling holes on the pressure side and the suction side of the blade.

6. The turbine rotor blade of claim 5, and further comprising:

the second legs of the two nested serpentine flow circuits each include a row of film cooling holes on the pressure side of the blade.

7. The turbine rotor blade of claim 6, and further comprising:

the third legs of the two nested serpentine flow circuits each include a row of film cooling holes on the pressure side of the blade.

8. A turbine airfoil used in a gas turbine engine, the airfoil having a leading edge and a trailing edge, the airfoil also having a pressure side and a suction side and an internal cooling air passage to provide cooling for the airfoil, the turbine airfoil comprising:

two triple-pass serpentine flow cooling circuits nested together and in parallel along substantially the entire airfoil portion;

the two nested serpentine flow cooling circuits are separated by substantially radial extending ribs; and

,

the rib in the third legs of the two nested serpentine flow circuits include a plurality of cross-over holes to allow for the cooling air from one of the nested circuits to cross over into the other of the two nested circuits.

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

the two triple-pass serpentine flow cooling circuits are both aft flowing circuits.

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

the last legs of the nested serpentine flow cooling circuits each comprises at least one blade tip cooling hole to discharge cooling air from the respective last leg to the blade tip.

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

the forward-most serpentine circuit of the two nested serpentine flow circuits includes a blade tip channel extending along the blade tip and connecting the first leg to the second leg of the serpentine flow circuit.

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

the blade tip channel includes a plurality of blade tip cooling holes to discharge cooling air from the serpentine flow circuit to the blade tip.

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

a plurality of cooling slots arranged along the trailing edge of the airfoil and in fluid communication with the last leg of the aft-most serpentine flow circuit of the two nested serpentine flow circuits such that cooling air from the last leg flows out the slots.