Natural frequency tuning of gas turbine engine blades

• US 7,252,481 B2
• Filed: 05/14/2004
• Issued: 08/07/2007
• Est. Priority Date: 05/14/2004
• Status: Active Grant

• Current Assignee: Pratt & Whitney Canada Corporation (Rtx Corporation)
• Original Assignee: Pratt & Whitney Canada Corporation (Rtx Corporation)
• Inventors: Stone, Paul
• Primary Examiner(s): Nguyen; Ninh H.
• Application Number:
  US10/845,237
• Publication Number:
  US 20050254958A1
• Time in Patent Office: 1,180 Days
• Field of Search: 416/144, 416/193.A, 416/215, 416/216, 416/218, 416/219.R, 416/220.R, 416/221, 416/239, 416/248, 416/500, 415/119, 294/011, 294/070.7, 298/892.1, 298/892.2, 298/892.3, 298/897
• US Class Current: 416/239
• CPC Class Codes: F01D 5/02 Blade-carrying members, e.g. rotors rotors of non-bladed type F01D1/34; stators F01D9/00 ; selecting particular materials F01D5/28
• CPC Class Codes: F01D 5/021 for flow machines or engines with only one axial stage for more than one stage F01D5/06
• CPC Class Codes: F01D 5/10 Anti- vibration means specially adapted for radial flow machines or engines F01D5/04
• 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 5/16 for counteracting blade vibration
• CPC Class Codes: F01D 5/3007 of axial insertion type
• CPC Class Codes: F05D 2230/10 by removing material
• CPC Class Codes: F05D 2260/96 Preventing, counteracting or reducing vibration or noise
• CPC Class Codes: Y10S 416/50 Vibration damping features

Abstract

A tuning notch is defined preferably in the back of a blade root to tune the blade natural frequency in a gas turbine engine.

Claims

1. A gas turbine engine blade adapted to be mounted in a blade attachment slot, defined between a front face and a back face of a rotor disc mounted for rotation about an axis, the blade comprising:

a platform having a top surface and a bottom surface, an airfoil extending upwardly from said top surface of said platform, a root extending downwardly from said bottom surface of said platform, said root having a disc engaging portion adapted to be received in the blade attachment slot, wherein said blade has a natural frequency, and wherein said natural frequency is tuned by a tuning notch defined in a back side of the root radially outwardly of said disc engaging portion and of the blade attachment slot when the blade is mounted therein, and wherein said tuning notch extends axially inwardly relative to the back face of the rotor disc and the blade attachment slot when the blade is operatively installed on the disc.

2. A gas turbine engine blade as defined in claim 1, wherein said tuning notch is defined immediately below said platform.

3. A gas turbine engine blade as defined in claim 1, wherein said tuning notch has a rounded profile.

4. A gas turbine engine blade as defined in claim 1, wherein said gas turbine engine blade is a swept fan blade.

5. A gas turbine engine blade as defined in claim 1, wherein said root has an axially extending dovetail, and wherein said tuning notch is radially spaced from said axially extending dovetail.

6. A gas turbine engine fan comprising a rotor disc mounted for rotation about an axis and carrying a plurality of blades, each of said blades having a root depending from a bottom surface of a platform, said root having a disc engaging portion for engagement in a corresponding blade attachment slot defined in the rotor disc, and wherein each of said blades has a natural frequency, said natural frequency being tuned by a notch defined in a back side of said root radially outwardly of said disc engaging portion and said blade attachment slot and wherein the notch extends axially inwardly relative to the back side of the disc and the blade attachment slot.

7. A gas turbine engine fan as defined in claim 6, wherein said notch is located next to said platform away from a bottom distal end of said root.

8. A gas turbine engine fan as defined in claim 7, wherein said fan is a swept fan.

9. A gas turbine engine fan as defined in claim 6, wherein said notch has a rounded profile.

10. A method of tuning the natural frequency of a gas turbine engine blade adapted to be mounted to a rotor disc mounted for rotation about an axis and having a back face, the blade having a root depending from a platform, the root having a disc engaging portion, the method comprising the step of:

ascertaining aerodynamic excitation frequencies to which the blade is subject during use , adjusting the natural frequency of the blade such as to avoid the aerodynamic excitation frequencies by machining a notch in a back surface of the root of the blade between the platform and the disc engaging, the notch extending axially inwardly relative to the back face of the disc when the blade is mounted thereto.

11. A method as defined in claim 10, wherein the notch is located immediately below the platform.

12. A method as defined in claim 10, wherein the notch has a rounded profile.

13. A method of tuning a gas turbine engine blade received in an axially extending blade attachment slot defined in a disc mounted for rotations about an axis, the blade having a platform and a root depending therefrom, the root having a blade fixation portion adapted to be engaged with a disk, the method comprising the steps of:

a) ascertaining aerodynamic excitation frequencies to which the blade is subject during use, and b) adjusting the natural frequency of the blade in order to avoid the aerodynamic excitation frequencies by defining a notch in a back surface or the root portion of the blade radially outwardly of the blade attachment slot and axially inwardly with respect thereto.