Seal support disk and assembly

Patent metadata

Field	Value
Publication number	US-10060279-B2
Application number	US-201314652711-A
Country	US
Kind code	B2
Filing date	Dec 23, 2013
Priority date	Dec 29, 2012
Publication date	Aug 28, 2018
Grant date	Aug 28, 2018

Abstract

An assembly for a gas turbine engine includes a first module, a second module interconnected with the first module, a first gas turbine component, and a seal assembly. The first gas turbine component includes a body extending generally radially between an inner mounting portion and an outer seal carrier portion. The inner mounting portion is fastened to the first module such that the first gas turbine component forms a boundary between a first annular cavity in the first module, and a second annular cavity in the second module. The seal assembly is mounted to the seal carrier portion of the first gas turbine component, and includes a flow diverter assembly having a flow diverter and a finger seal commonly fastened to a first axial side of the seal carrier portion.

First claim

The invention claimed is:

1. An assembly for a gas turbine engine, comprising:
a first module comprising:
a turbine exhaust case assembly including a fairing assembly secured over annular surfaces of an aftmost engine support frame, the fairing assembly defining a first main gas flow passage annularly between an inner frame platform and an outer frame casing and around a plurality of frame strut liners disposed over a corresponding plurality of radially extending frame support struts; and
a first annular leakage cavity radially inward of the fairing assembly and the first main gas flow passage;

a second module comprising:
a free power turbine assembly removably interconnected with the first module immediately downstream thereof, the free power turbine assembly including a second main gas flow passage in flow communication with the first main gas flow passage, the second main gas flow passage having a stator inlet vane airfoil axially adjacent to the fairing assembly, and a free power turbine rotor airfoil extending radially through the second portion of the main gas flow passage downstream of the stator inlet vane airfoil; and
a second annular leakage cavity radially inward of the second main gas flow passage, axially adjacent to the first annular cavity when the first and second modules are interconnected;

a seal support disk including a ring-shaped body extending generally radially between an inner mounting portion and an outer seal carrier portion, the inner mounting portion fastened to the inner frame platform of the first module such that the seal support disk body forms a boundary between the first annular leakage cavity in the first module, and the second annular leakage cavity in the second module when the first and second modules are interconnected; and
a seal assembly mounted to the seal carrier portion of the seal support disk for limiting secondary air leakage flows between the first leakage cavity and the second leakage cavity proximate the first and second main gas flow passages;
wherein the seal support disk retains the seal assembly at a location radially inward from the fairing assembly and the seal assembly includes a flow diverter assembly having a flow diverter and a finger seal commonly fastened to an axial side of the seal carrier portion facing the second module.

2. The assembly of claim 1 , further comprising a W-seal resiliently retained against a land formed on an axial side of the seal carrier portion facing the first module, opposite the seal assembly.

3. The assembly of claim 2 , wherein the W-seal is resiliently retained by an external surface of the fairing assembly.

4. The assembly of claim 1 , wherein the finger seal includes a fixed end and a free end, the fixed end fastened between the flow divider and the seal carrier portion, and the free end contacting a surface of a gas turbine component connected to the second module.

5. The assembly of claim 4 , wherein the component connected to the second module comprises a labyrinth seal.

6. A seal assembly for a gas turbine engine, the seal assembly comprising:
a seal support disk including a ring-shaped body extending generally radially between a radially inner mounting portion and a radially outer seal carrier portion, the inner mounting portion adapted to be fastened to an inner frame platform of an aftmost annular engine support frame and comprising a snap ring and a first fastenable flange, the body sized to extend generally radially between the inner platform, and a fairing assembly secured around the annular engine support frame; and
a seal assembly mounted to the outer seal carrier portion of the seal support disk, the seal assembly comprising a flow diverter assembly secured around a first axial side of the seal carrier portion, away from the aftmost engine support frame when installed thereto, the flow diverter assembly including a finger seal having a fixed end fastened between a flow diverter element and the first axial side of the outer seal carrier portion, the flow diverter element including a diverter arm adapted to extend away from the aftmost engine support frame when installed thereto.

7. The seal assembly of claim 6 , the seal assembly further comprising a W-seal resiliently retaining against a seal land disposed on a second axial side of the outer seal carrier portion opposite the first axial side.

8. The seal assembly of claim 6 , wherein the mounting portion of the seal support disk further comprises a second fastenable flange for fastening the seal support disk to a surface of the inner frame platform for a gas turbine engine.

9. The seal support assembly of claim 8 , wherein the inner frame platform is for a turbine exhaust case supporting an aft end of the gas turbine engine.

10. The seal support assembly of claim 8 , wherein the seal support disk, the flow diverter, and the finger seal are installable or removable as a single unit from the surface of the inner frame platform.

11. The seal support assembly of claim 6 , further comprising a W-seal land, the W-seal land having a radial portion including a second axial side of the radial flange, and an axial portion perpendicular to the radial portion.

12. The seal support assembly of claim 6 , wherein the inner mounting portion of the seal support disk comprises a boltable flange for removably securing the seal support disk to the inner frame platform.

Assignees

• United Technologies Corp

Inventors

• Vo Tuan David
• Scott Jonathan Ariel

Classifications

• F01D11/005

  Sealing means between non relatively rotating elements · CPC title

• F01D25/24

  Casings (modified for heating or cooling F01D25/14); Casing parts, e.g. diaphragms, casing fastenings (casings for rotary machines or engines in general F16M {; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045}) · CPC title

• F16J15/0887

  the sealing effect being obtained by elastic deformation of the packing · CPC title

• F01D25/243

  Flange connections; Bolting arrangements (F01D25/265 takes precedence) · CPC title

• F05D2240/59

  Lamellar seals · CPC title