Wear resistant frame liner joint assembly for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-2017191669-A1
Application number	US-201514984733-A
Country	US
Kind code	A1
Filing date	Dec 30, 2015
Priority date	Dec 30, 2015
Publication date	Jul 6, 2017
Grant date	—

Abstract

A tripod joint assembly for connecting first and second overlapping panel segments of a flowpath liner in a gas turbine engine includes a threaded fastener extending through an opening in the first overlapping panel segment and adjacent to an outer segment edge of the second overlapping panel segment disposed on the first overlapping segment. The assembly further includes a tripod plate having first and second plate edges and an access hole therebetween. The first plate edge contacts the first overlapping panel segment, the second plate edge contacts the outer segment edge of the second overlapping panel segment. The access hole is disposed around the threaded fastener. First and second washers are disposed around the threaded fastener, the first washer on the tripod plate opposite to the overlapping panel segments, and the second washer on the first washer opposite to the tripod plate. A threaded locknut secures the assembly.

First claim

What is claimed is:

1 . A tripod joint assembly for connecting first and second overlapping panel segments of a flowpath liner in a gas turbine engine, the tripod joint assembly comprising:
a threaded fastener extending through an opening in the first overlapping panel segment and adjacent an outer segment edge of the second overlapping panel segment disposed on the first overlapping segment; a tripod plate having first and second plate edges and an access hole therebetween, the first plate edge contacting the first overlapping panel segment, the second plate edge contacting the outer segment edge of the second overlapping panel segment, and the access hole disposed around the threaded fastener; a first washer disposed around the threaded fastener on the tripod plate opposite the first and second overlapping panel segments; a second washer disposed around the threaded fastener on the first washer opposite the tripod plate; and a threaded locknut secured to the threaded fastener and contacting the second washer opposite the first washer.

2 . The tripod joint assembly according to claim 1 , wherein the second washer is a spring washer that inwardly angles away from the first washer.

3 . The tripod joint assembly according to claim 2 , wherein the threaded locknut is configured to apply a spring bias to the second washer against the first washer.

4 . The tripod joint assembly according to claim 1 , wherein the tripod plate includes a flat surface opposite the first and second overlapping panel segments, and wherein the tripod plate flat surface includes a concave seat around the access hole.

5 . The tripod joint assembly according to claim 4 , wherein the first washer includes a convex surface configured to mate with the concave seat of the tripod plate.

6 . The tripod joint assembly according to claim 1 , wherein the first washer further includes a substantially flat surface opposite the convex surface and including an annular lip disposed in the vicinity of the threaded fastener and facing the second washer.

7 . The tripod joint assembly according to claim 1 , wherein the first overlapping panel segment is a fairing platform.

8 . The tripod joint assembly according to claim 7 , wherein the fairing platform includes a protruding mounting base configured to contact the first plate edge of the tripod plate.

9 . The tripod joint assembly according to claim 1 , wherein the first plate edge of the tripod plate includes a protrusion, and the first overlapping panel segment includes a locating indentation configured to receive a portion of the protrusion.

10 . The tripod joint assembly according to claim 1 , wherein the second overlapping panel segment includes a contact surface opposite the first overlapping panel segment, and wherein the second plate edge of the tripod plate includes a plate engagement surface having two buttons configured to engage the contact surface of the second overlapping panel segment.

11 . The tripod joint assembly according to claim 10 , wherein the two buttons are convex with respect to the plate engagement surface.

12 . The tripod joint assembly according to claim 1 , wherein the first overlapping panel segment includes an expansion surface configured to slidably engage a first surface of the outer segment edge of the second overlapping panel segment adjacent the expansion surface, and wherein the expansion surface and adjacent first surface each include a wear-resistant coating disposed between the first and second overlapping panel segments.

13 . The tripod joint assembly according to claim 12 , wherein the tripod plate includes an engagement surface facing the second overlapping panel segment and having a wear-resistant coating disposed thereon, and wherein the outer segment edge of the second overlapping panel segment includes a second surface opposite the first surface, and having a wear-resistant coating disposed thereon between the tripod plate and the outer segment edge.

14 . The tripod joint assembly according to claim 12 , wherein the tripod plate is unitary and comprises a wear-resistant material.

15 . A flowpath liner assembly for a gas turbine engine, the flowpath liner assembly comprising:
an annular forward hanger; an annular aft hanger; a plurality of panel segments disposed radially between the annular forward hanger and the annular aft hanger, each of the plurality of panel segments having first and second opposing engagement edges extending in the radial direction; a plurality of fairing platforms disposed radially between the annular forward hanger and the annular aft hanger, each of the plurality of fairing platforms including first and second opposing extension edges extending in the radial direction, the plurality of fairing platforms configured to be disposed in an alternating arrangement with the plurality of panel segments, and each of the first and second opposing extension edges configured to overlap with a respective adjacent engagement edge of the plurality of panel segments; and a plurality of tripod joint assemblies configured to respectively couple each of the extension edges with a respective adjacent engagement edge, each of the plurality of tripod joint assemblies comprising: a threaded fastener fixedly attached to a respective engagement edge; a tripod plate comprising a wear-resistant material and having first and second plate edges configured to contact an extension edge and an adjacent engagement edge, respectively; a spring washer disposed around the threaded fastener on the tripod plate opposite the respective extension edge and adjacent engagement edge; and a threaded locknut configured to apply a bias to the spring washer when secured to the threaded fastener.

16 . The flowpath liner assembly according to claim 15 , wherein each of the plurality of fairing platforms includes at least one hollow airfoil configured to allow air communication therethrough.

17 . The flowpath liner assembly according to claim 15 , wherein the spring washer comprises a first washer configured to couple with the tripod plate about the threaded fastener and a second washer between the first washer and the threaded locknut, the second washer inwardly angled toward the threaded fastener and away from the first washer.

18 . The flowpath liner assembly according to claim 15 , wherein the tripod plate is unitary and fabricated from wear-resistant material.

19 . The flowpath liner assembly according to claim 15 , wherein each of the pluralities of extension edges and engagement edges comprise a wear-resistant coating on respective contacting surfaces therebetween.

20 . A gas turbine engine including a high pressure turbine, a high pressure turbine rotor shaft, and a low pressure turbine, the gas turbine engine comprising:
an annular center frame disposed between the high pressure turbine and the low pressure turbine, the annular center frame configured to support the high pressure turbine shaft a flowpath liner disposed between the high pressure turbine and the low pressure turbine, the flowpath liner fixedly attached to the annular center frame and configured to shield the annular center frame from exposure to high temperature gases from the high pressure turbine, the flowpath liner comprising:
a plurality of radially disposed panel segments circumferentially arranged around the annular center frame;
a plurality of radially disposed fairing platforms circumferentially arranged around the annular center frame to alternate with adjacent o

Assignees

• Gen Electric

Inventors

• Oswald Eric Robert
• Ryczek Scott Patrick
• Bosel Tod Kenneth
• Czachor Robert

Classifications

• F16B39/28

  by special members on, or shape of, the nut or bolt (F16B39/26 takes precedence; locknuts F16B39/12) · CPC title

• F23R3/50

  Combustion chambers comprising an annular flame tube within an annular casing (toroidal combustion chambers F23R3/52) · CPC title

• F23R3/60 Primary

  Support structures; Attaching or mounting means · CPC title

• F16B5/02

  by means of fastening members using screw-thread ({F16B5/0004 takes precedence}; construction of screw-threaded connections F16B25/00 - F16B39/00) · CPC title

• F05D2230/642

  using maintaining alignment while permitting differential dilatation · CPC title