Hollow core airfoil stiffener rib

• US 9,091,175 B2
• Filed: 08/24/2011
• Issued: 07/28/2015
• Est. Priority Date: 08/24/2011
• Status: Active Grant

• Current Assignee: Pratt & Whitney Canada Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: Pratt & Whitney Canada Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Durocher, Eric, Demers, Maxime
• Primary Examiner(s): Wiehe, Nathaniel
• Assistant Examiner(s): Brownson, Jeffrey A
• Application Number:
  US13/216,613
• Publication Number:
  US 20130052029A1
• Time in Patent Office: 1,434 Days
• US Class Current: 1/1
• 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 5/20 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
• CPC Class Codes: Y10T 29/49339 Hollow blade

Abstract

A stiffener rib for a non-cooled, hollow core airfoil of a turbine blade is described. The stiffener rib is constituted by an elongated solid metal piece dimensioned for securement in a hollow region of a core portion of the airfoil. The stiffener rib is shaped and oriented upwards from a leading edge of the airfoil at a predetermined calculated angle to minimize mode 2 deformation of the blade at a trailing edge thereof while improving the rigidity of the turbine blade.

Claims

1. A gas turbine engine blade comprising an airfoil extending from a platform to a tip between a leading edge and a trailing edge, said airfoil having a hollow core portion adjacent said leading edge and spaced-apart from said trailing edge in a chordwise direction, the hollow core portion extending from the platform to the tip, and a stiffener rib provided in the hollow core portion of said airfoil and extending across a thickness of the airfoil between opposed side walls of the hollow core portion, the stiffener rib being positioned closer to the leading edge than the trailing edge in the chordwise direction, the stiffener rib having an elongated cross-section including a longitudinal length L greater than a width W, the stiffener rib having a longitudinal axis which is angled to have a radial upward component and an axial component in a direction away from the leading edge of the airfoil, the longitudinal axis of the stiffener rib extending through the trailing edge at a location adjacent to a trailing edge tip corner where the trailing edge meets the tip of the blade.

2. The blade defined in claim 1, wherein the stiffener rib is positioned and oriented to minimize mode 2 deformation at the trailing edge, and wherein the stiffener rib extends at about 20°

to 60°

degrees from a reference axis extending transverse to a tip axis of the leading edge.

3. The blade defined in claim 2, wherein the stiffener rib extends at about 33°

degrees from the reference axis.

4. The blade defined in claim 1, wherein said stiffener rib is an elongated hollow rectangular rib having opposed convex end edges.

5. The blade defined in claim 2, wherein the distance T between the longitudinal axis of the stiffener rib and an axis parallel thereto and extending through the trailing edge tip corner is equal to or less than 0.275 inches.

6. The gas turbine engine defined in claim 1, wherein the stiffener rib is spaced from the leading edge by a distance S of about 0.175±

0.075 inches.

7. A stiffener rib for a non-cooled, hollow core airfoil of a turbine or compressor blade, said stiffener rib being constituted by an elongated solid metal piece positioned in a hollow region of a hollow core portion of said airfoil adjacent to a leading edge of the airfoil and spaced-apart from a trailing edge of the airfoil in a chordwise direction, and said stiffener rib being shaped and oriented upwards from a leading edge of said airfoil at a predetermined calculated angle to minimize mode 2 deformation of said blade at a trailing edge thereof while improving the rigidity of said turbine blade, and wherein the stiffener rib is positioned closer to the leading edge than the trailing edge in a chordwise direction.

8. The stiffener rib as claimed in claim 7, wherein said predetermined calculated angle is in the range of from about 20°

to 60°

degrees from a reference axis extending transverse to a tip axis of said leading edge.

9. The stiffener rib as claimed in claim 8, wherein said predetermined angle is equal to about 33°

degrees.

10. The stiffener rib as claimed in claim 7, wherein said stiffener rib extends across the thickness of said hollow core airfoil and secured between opposed side walls of said airfoil.

11. The stiffener rib as claimed in claim 7, wherein said stiffener rib is dimensioned to move the natural frequency mode 2 out of running range of said turbine blade.

12. The stiffener rib as claimed in claim 11, wherein said stiffener rib is dimensioned in length to tune the frequency of said turbine blade and to permit the flow of air throughout said hollow core.

13. The stiffener rib as claimed in claim 7, wherein said stiffener rib is an elongated rectangular rib having opposed convex end edges.

14. A method of minimizing deflection of a trailing edge of a non-cooled hollow core airfoil subject to mode-2 deformation, comprising the steps of:

i) calculating by dynamic analytical model for mode 2 the dimension and orientation of a stiffener rib for location in a hollow region of a core portion of said hollow core airfoil adjacent to a leading edge of the airfoil and spaced-apart from the trailing edge of the airfoil in a chordwise direction, and

ii) securing said stiffener rib across opposed side walls of said airfoil and oriented angularly upwards from a leading edge of said airfoil at a predetermined angle to minimize deflection of said blade at said trailing edge in the running range of said airfoil and improve the rigidity thereof, the stiffener rib being positioned closer to the leading edge than the trailing edge in a chordwise direction.

15. The method as claimed in claim 14, wherein said step (ii) comprises securing said stiffener rib at a predetermined calculated angle in the range of from about 20°

to 60°

degrees from a reference axis extending transverse to a tip axis of said leading edge.

16. The method as claimed in claim 15, wherein said calculated angle is approximately 33°

degrees.