Turbine blade having tip slot

• US 5,503,527 A
• Filed: 12/19/1994
• Issued: 04/02/1996
• Est. Priority Date: 12/19/1994
• Status: Expired due to Term

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Pietraszkiewicz, Edward F., Prakash, Chander, Zerkle, Ronald D., Lee, Ching-Pang
• Primary Examiner(s): Look, Edward K.
• Assistant Examiner(s): LARSON, JAMES
• Application Number:
  US08/329,750
• Time in Patent Office: 470 Days
• Field of Search: 416/91, 416/90 R, 416/96 R, 416/96 A, 416/97 R, 416/231 R, 416/231 B, 415/171.1, 415/173.1
• US Class Current: 416/91
• CPC Class Codes: F01D 5/20 Specially-shaped blade tips to seal space between tips and stator F01D5/225 takes precedence
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A gas turbine engine rotor blade includes an airfoil having first and second sidewalls joined together at leading and trailing edges. First and second tip walls extend from adjacent the leading edge along the respective first and second sidewalls to adjacent the trailing edge and are spaced apart to define a tip cavity therebetween. A first notch is disposed in the first tip wall adjacent to the leading edge for channeling into the tip cavity a portion of combustion gases flowable over the airfoil for reducing the heating effect of the gases on the blade tip. In a preferred embodiment, a second notch is disposed adjacent to the trailing edge for promoting flow through the tip cavity from the first notch.

Claims

1. A gas turbine engine rotor blade comprising an airfoil and integral dovetail for mounting said airfoil to a rotor disk, said airfoil including:

first and second sidewalls joined together at a leading edge and at a trailing edge, and extending from a root disposed at said dovetail to a tip plate, and a cooling chamber disposed in said airfoil for receiving cooling fluid through said dovetail;

a first tip wall extending upwardly from said tip plate along said airfoil first sidewall from adjacent said leading edge to adjacent said trailing edge;

a second tip wall extending upwardly from said tip plate along said airfoil second sidewall from said leading edge to adjacent said trailing edge, and being spaced from said first tip wall to define an open-top tip cavity therebetween; and

a first notch disposed in said first tip wall adjacent said airfoil leading edge for channeling into said tip cavity a portion of combustion gas flowable over said airfoil.

2. A blade according to claim 1 wherein said airfoil is configured for effecting a pressure distribution along said first and second tip walls from said leading edge to said trailing edge, and said first notch is disposed adjacent said leading edge for channeling said gas portion inside said tip cavity due to differential pressure across said first notch.

3. A blade according to claim 1 further comprising a second notch disposed in one of said first and second tip walls adjacent said airfoil trailing edge for discharging said gas portion from said tip cavity and promoting crossflow of said gas portion from said first notch through said tip cavity to said second notch.

4. A blade according to claim 3 wherein both said first and second notches are disposed in said airfoil first tipwall.

5. A blade according to claim 4 wherein said airfoil first sidewall defines a suction side of said airfoil, and said second sidewall defines a pressure side of said airfoil.

6. A blade according to claim 5 wherein said first and second tip walls are substantially equal in height.

7. A blade according to claim 6 wherein said first notch extends at least partly into said first tip wall toward said tip plate.

8. A blade according to claim 6 wherein said second notch extends completely into said first tip wall to said tip plate.

9. A blade according to claim 6 wherein said second tip wall extends completely to said airfoil trailing edge, and said first tip wall ends short of said airfoil trailing edge, and is spaced from said second tip wall for defining said second notch therebetween.