Interblade damper and seal for turbomachinery rotor

• US 4,101,245 A
• Filed: 12/27/1976
• Issued: 07/18/1978
• Est. Priority Date: 12/27/1976
• Status: Expired due to Term

• Current Assignee: United Technologies Corporation (Rtx Corporation)
• Original Assignee: United Technologies Corporation (Rtx Corporation)
• Inventors: Hess, John R., Asplund, Herbert Frederick
• Primary Examiner(s): Powell, Jr., Everette A.
• Application Number:
  US05/754,666
• Time in Patent Office: 568 Days
• Field of Search: 416/219, 416/221, 416/190, 416/193 A, 416/500, 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: F01D 5/3007 of axial insertion type
• CPC Class Codes: Y10S 416/50 Vibration damping features

Abstract

An interblade seal and vibration damper to be positioned in the damper cavity defined between a rotor disc, adjacent blades and adjacent blade platforms so as to seal across an interplatform gap by providing line contact between the damper and the platforms on opposite sides thereof for the full axial dimension of the cavity and with the damper shaped so as to have a low center of gravity for operational stability and which damper also responds to centrifugal force during rotor operation to establish damping friction between said damper and said platforms when the platforms move circumferentially.

Claims

1. A turbomachinery rotor comprising:

(A) a central disc adapted to be rotated about an axis of rotation extending axially of the rotor,

(B) a plurality of blades connected to the periphery of said disc to form a circumferential array of blades about the periphery of the disc and with each blade having,

(1) a platform extending generally circumferentially from opposite sides of each blade so that platforms of adjacent blades terminate in close circumferential proximity to define a circumferential gap of selected size between adjacent blade platforms and so that the disc and adjacent blades and their platforms cooperate to define a blade damper cavity therebetween communicating with said gap, and

(a) each platform including a flat surface adjacent the blade and generally facing the disc axis and extending for substantially the full axial dimension of the cavity to define a part of said cavity and positioned so that the blade platform flat surfaces of adjacent blades in each cavity are parallel and lie in the same plane, which plane is perpendicular to a radial line extending from said axis of rotation and passing midway between said flat surfaces in each cavity and

(b) a recessed portion extending for substantially the full axial dimension of the blade damper cavity and opening thereinto and into the platform circumferential gap so that said recessed portions of adjacent platforms cooperate to define a continuous recess extending substantially for the full axial dimension of the damper cavity and opening thereinto,

(C) a one-piece blade damper and seal located in said blade damper cavity and extending for substantially the full axial dimension thereof and overlapping said flat surfaces of adjacent blade platforms and having,

(1) rails of curved cross-section extending in parallel relationship for the full axial dimension of the damper on opposite lateral sides thereof so that said rails contact adjacent platform single plane, flat surfaces in line contact for substantially the full axial dimension of the cavity,

(2) a solid central portion of the blade damper extending between said rails and across said gap and outwardly into the blade platform recess so that the blade damper center of gravity is located on or near said platform flat surfaces so that, in response to centrifugal force, the blade damper rails bear in line contact against adjacent blade platform single plane, flat surfaces for substantially the full axial dimension of the blade damper cavity to cooperate with the central portion to seal said cavity from said gap to thereby prevent recirculation of hot gases through said gap and around said damper into said blade damper cavity, and so that as each blade platform moves circumferentially during rotor operation, the line contact between the damper rail and the platform flat surface will establish friction therebetween to dampen blade motion.

2. A rotor according to claim 1 wherein said blade damper and seal has a centerline and wherein said damper is symmetrically shaped on opposite lateral sides thereof and of uniform construction on opposite sides thereof so that the damper is of uniform axial weight distribution and thereby provides a uniform axial damping and sealing force to the blades.

3. A rotor according to claim 2 wherein said blade platforms are shaped to be thicker at said flat surface than at said recessed portion so that the platform carries blade damper loads at said thicker flat section.

4. A rotor according to claim 3 wherein said blade damper and seal cavity and said platform continuous recess are axially extending and of substantially consistent lateral cross sectional shape and so that said blade damper is axially extending and of symmetric lateral cross section along its axis so that said blade damper and seal may be assembled into said blade damper cavity and platform continuous recess from either axial side of said rotor either with blades in place or during assembly of blades.

5. A rotor according to claim 4 wherein each blade includes a radially extending neck or shank portion radially inboard of the blade platform and which blades are shaped and sized so that with adjacent blades assembled onto the central disc, the circumferential spacing between adjacent blade neck portions is slightly larger than the damper lateral dimension.

6. A rotor according to claim 5 and including means to retain said blades axially with respect to said disc and means to retain said damper and seal axially within said damper cavity.

7. A rotor according to claim 6 wherein said retaining means constitute side plates attached to opposite sides of said disc and extending radially outwardly therefrom to be positioned at opposite axial ends of said blades and said damper and seal for axial retention thereof and for partially defining said damper cavity.

8. A rotor according to claim 7 and including means to connect said blades to said disc including a plurality of radially extending and circumferentially spaced lug members projecting from the periphery of the disc and being shaped in circumferential cross section to form an axially extending male fir-tree connecting member and so that adjacent lugs define an axially extending female fir-tree connection recess, and wherein each blade has a fir-tree shaped root portion shaped to be snugly received in the female fir-tree connection recess between adjacent disc lugs, and wherein each disc lug has a circumferentially extending outer radial surface of selected radial spacing from said platform flat surfaces with said blades so retained from said disc.

9. A rotor according to claim 8 wherein said damper and seal has radially inwardly extending tabs at the opposite axial ends thereof and sized to be spaced a selected radial distance from said lug outer surface when said damper is positioned in said damper cavity so that said tabs will come into contact with said lug outer surface if the damper attempts to pivot on either of the damper rails.

10. A rotor according to claim 9 wherein said damper and seal is shaped to have a laterally extending frame extending between said rails at the opposite axial ends thereof so that said frame members and said rails form a box shaped strength frame about the periphery of said damper and seal to provide structural rigidity thereto.

11. A rotor according to claim 10 wherein said blades are shroudless.

12. A rotor according to claim 9 wherein the axial clearance between said damper and seal and said side plates is about 0.003 inches.

13. A rotor according to claim 1 wherein said rail members and said platform flat surfaces are finish machined and wherein said blade damper and seal is shaped so that the two lines of contact formed between the blade damper rails and the platform flat surfaces within a given blade damper cavity are parallel to one another and to said disc axis.