Turbine blade with film cooling slots

• US 8,231,330 B1
• Filed: 05/15/2009
• Issued: 07/31/2012
• Est. Priority Date: 05/15/2009
• 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: Liang, George
• Primary Examiner(s): Lebentritt, Michael
• Application Number:
  US12/466,566
• Time in Patent Office: 1,173 Days
• Field of Search: 415/115, 415/116, 416/96.A, 416/96.R, 416/97.R, 416/232, 416/241.R
• US Class Current: 415/115
• CPC Class Codes: F01D 5/186 Film cooling F01D5/187 takes precedence
• CPC Class Codes: F05D 2240/304 related to the trailing edge of a rotor blade
• CPC Class Codes: F05D 2240/305 related to the pressure side of a rotor blade

Abstract

A turbine rotor blade with a row of exit slots adjacent to a trailing edge region of the airfoil that extends from the platform to the blade tip, where the row of exit slots is formed into three groups that include an upper span group, a mid-span group and a lower span group. The upper span group discharges film cooling air upward with respect to the airfoil chordwise direction, the mid-span group discharges along the chordwise direction, and the lower span group discharges in a direction downward with respect to the chordwise direction. Each exit slot is formed with a plurality of metering inlet holes that discharge into a first diffusion section and then a second diffusion section.

Claims

1. An air cooled turbine rotor blade comprising:

an airfoil having a leading edge and a trailing edge;

the airfoil having a pressure side wall and a suction side wall both extending between the leading edge and the trailing edge;

a row of exit slots arranged along the pressure side wall of the airfoil adjacent to the trailing edge region of the airfoil;

the row of exit slots extending from adjacent to a platform of the blade to adjacent to a tip of the blade;

the row of exit slots including an upper span section of slots, a mid-span section of slots and a lower span section of slot; and

,

the upper span exit slots discharging film cooling air in a direction toward the blade tip, the mid-span exit slots discharging film cooling air in a chordwise direction of the airfoil, and the lower span exit slots discharging film cooling air in a direction toward the platform.

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

the exit slots each include a metering inlet section with a plurality of metering holes that open into a diffusion section.

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

the diffusion section includes a first diffusion section immediately downstream from the metering section and a second diffusion section immediately downstream from the first diffusion section.

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

the first diffusion section includes an expansion of from 7 to 13 degrees on a downstream wall with respect to an axis of the metering holes.

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

the upper span exit slots have a radial outboard expansion of 0 to 3 degrees and a radial inboard expansion of from 7 to 13 degrees; and

,

the mid-span exit slots have a radial outboard expansion of 7 to 13 and a radial inboard expansion of from 7 to 13 degrees; and

,

the lower-span exit slots have a radial outboard expansion of 7 to 13 and a radial inboard expansion of from 0 to 3 degrees.

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

the upper span exit slots have a radial outboard expansion of 0 to 3 degrees and a radial inboard expansion of from 7 to 13 degrees; and

,

the mid-span exit slots have a radial outboard expansion of 7 to 13 and a radial inboard expansion of from 7 to 13 degrees; and

,

the lower-span exit slots have a radial outboard expansion of 7 to 13 and a radial inboard expansion of from 0 to 3 degrees.

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

the upper span exit slots have a discharge angle with respect to the airfoil spanwise radial direction of from 20 to 40 degrees;

the mid-chord span exit slots have a discharge angle with respect to the airfoil spanwise radial direction of from 80 to 100 degrees; and

,

the lower span exit slots have a discharge angle with respect to the airfoil spanwise radial direction of from 110 to 130 degrees.

8. The air cooled turbine rotor blade of claim 1, and further comprising:

the upper span exit slots have a discharge angle with respect to the airfoil spanwise radial direction of around 30 degrees;

the mid-chord span exit slots have a discharge angle with respect to the airfoil spanwise radial direction of around 90 degrees; and

,

the lower span exit slots have a discharge angle with respect to the airfoil spanwise radial direction of around 120 degrees.