Turbine blade plateform sealing and vibration damping apparatus

• US 4,872,812 A
• Filed: 08/05/1987
• Issued: 10/10/1989
• Est. Priority Date: 08/05/1987
• Status: Expired due to Term

• Current Assignee: General Electric Company, Kimberly-Clark Worldwide Incorporated (Kimberly-Clark Corporation)
• Original Assignee: General Electric Company
• Inventors: Litzinger, William A., Hendley, David G.
• Primary Examiner(s): Powell, Jr., Everette A.
• Application Number:
  US07/081,773
• Time in Patent Office: 797 Days
• Field of Search: 416/193 A, 416/193 R, 416/190, 416/500, 416/219 R, 416/220 R, 416/191
• US Class Current: 416/190
• CPC Class Codes: F01D 11/006 Sealing the gap between rotor blades or blades and rotor
• CPC Class Codes: F01D 11/008 by spacer elements between the blades, e.g. independent interblade platforms
• CPC Class Codes: F01D 5/22 Blade-to-blade connections, e.g. for damping vibrations
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft
• CPC Class Codes: Y10S 416/50 Vibration damping features

Abstract

A gas turbine rotor blade platform sealing and damping system has elongated symmetrical insert elements of equilateral triangular cross-section loosely received within complementary shaped pockets at the spacing gaps between opposing convex and concave airfoil side edges of adjacently mounted blade platforms. The inserts and pockets are relatively configured to provide self-orientation of the inserts into gap sealing and vibration damping engagement with the platform edges when acted upon by centrifugal force due to rotor rotation. The convex platform edge is thickened at the point of closest proximity with the convex side of the airfoil. Alternative embodiments utilize insert grooves for increased leakage of cooling gas past the platform edges and incorporate a central bore for mass reduction.

Claims

1. An insert element to be loosely received between first and second opposing and converging edge surfaces of adjacent blade platforms of a rotor of a gas turbine engine and, in response to centrifugal forces acting thereon due to high rotor rotation speed, to seal a gap between the edge surfaces and to dampen vibration of the blades, said element comprising:

an elongated body having a longitudinal axis and at least three element surfaces configured and arranged symmetrically about said longitudinal axis so that, irrespective of the orientation with which said element is received between the platform edges, the centrifugal forces will drive one of said element surfaces into sealing engagement against the first edge surface and will drive another of said element surfaces into sealing engagement against the second edge surface.

2. An element as in claim 1, wherein said element surfaces are generally planar surfaces arranged about said longitudinal axis so that said insert element has a regular polygonal cross-section.

3. An element as in claim 2, wherein said cross-section is an equilateral triangle.

4. An element as in claim 3, wherein the ends of said insert element are rounded.

5. An element as in claim 1, wherein said insert element is provided with a groove running circumferentially across said surfaces about said axis.

6. An element as in claim 1, wherein said insert element is formed with a bore configured and positioned to reduce the mass of said element without interfering with the sealing engagement of said element with said edge surfaces.

7. Apparatus for sealing a gap between opposing edges of adjacent blades of a rotor of a gas turbine engine, and for damping vibration of the blades, wherein said adjacent blades comprise a first blade having a first platform edge, and a second blade having a second platform:

edge, said first and second blades being adjacently mounted on said rotor with said first and second platform edges opposingly positioned across a gap;

said apparatus comprising;

an elongated insert element loosely received between said first and second platform edges and having a longitudinal axis and a plurality of generally planar element surfaces configured and arranged symmetrically about said axis so that, irrespective of the angular orientation about said axis with which said insert element is received between said edges, centrifugal forces acting upon said insert element due to rotor rotation will drive one of said element surfaces into sealing engagement against said first platform edge and another of said element surfaces into sealing engagement against said second platform edge.

8. Apparatus as in claim 7, wherein said element surfaces are arranged about said axis so that said insert element has a regular polygonal cross-section.

9. Apparatus as in claim 8, wherein said cross-section is an equilateral triangle.

10. Apparatus as in claim 9, wherein said insert element is provided with a groove running circumferentially across said surfaces about said axis.

11. Apparatus as in claim 10 wherein said insert element is formed with a bore configured and positioned to reduce the mass of said element without interfering with the sealing engagement of said element surfaces against said edges.

12. A system for sealing a gap between opposing platform edges of adjacent blades of a rotor of a gas turbine engine, and for damping vibration of the blades, comprising:

a first blade having a first platform edge including a first generally planar edge surface;

a second blade having a second platform edge including a second generally planar edge surface;

said first and second blades being adjacently mounted on said rotor with said first and second platform edges opposingly positioned across a gap and with said first and second edge surfaces relatively configured and positioned to converge radially outwardly toward said gap at an angle of convergence α and

to define the radial outer boundaries of an elongated pocket formed between said platform edges; and

an elongated insert element loosely received within said pocket and having a plurality of generally planar element surfaces relatively configured and arranged about a central axis so that, irrespective of the orientation with which said insert element is received within said pocket, centrifugal forces acting upon said insert element due to rotor rotation will drive one of said element surfaces into sealing engagement against said first edge surface and another of said element surfaces into sealing engagement against said second edge surface.

13. A system as in claim 12, wherein said second platform edge further comprises a third generally planar edge surface located radially outward of said second edge surface and which is parallel to and opposes said first edge surface across said gap.

14. A system as in claim 13, wherein said third edge surface extends perimetally, radially down and around the sides of said second platform edge to define the sides of said pocket, and extends at least partially toward the center at the bottom of each side of said edge to define the radial inner boundaries of said pocket.

15. A system as in claim 13, wherein said element surfaces all have similar configuration and size and are arranged symmetrically about said central axis.

16. A system as in claim 15, wherein said insert element has an equilateral triangular cross-section, and wherein the angle of convergence α

is sixty degrees.

17. A system as in claim 13, wherein the width of said first edge surface exceeds the corresponding width of the third edge surface in the central areas of the opposing edges by an amount equal to at least one-half the width of said element surfaces.

18. A system as in claim 12, wherein said first and second blades comprise integrally formed airfoil and platform sections, said airfoil section having convex and concave sides;

wherein said first platform edge is on the convex airfoil side of said blade and said second platform edge is on the concave airfoil side of said blade; and

wherein said first edge surface includes a thickened portions at the point of closest proximity of said convex side of said airfoil to said first platform edge.