Flow diverter element and assembly

Patent metadata

Field	Value
Publication number	US-9850774-B2
Application number	US-201314653240-A
Country	US
Kind code	B2
Filing date	Dec 16, 2013
Priority date	Dec 29, 2012
Publication date	Dec 26, 2017
Grant date	Dec 26, 2017

Abstract

An assembly for a gas turbine engine, comprises a fairing assembly extending generally axially through a portion of the gas turbine engine, a first component disposed radially inward of the fairing assembly, a second component disposed axially adjacent to the first component, a flow diverter, and a finger seal. The flow diverter includes a mounting portion securing the flow diverter to the first component, and an arm extending in an axial direction from the mounting portion toward the second component. The finger seal includes a fixed end secured between the flow diverter mounting portion and the first component.

First claim

The invention claimed is:

1. An assembly for a gas turbine engine, comprising:
a fairing assembly extending generally axially through a portion of the gas turbine engine;
a first component comprising a radially extending seal support ring secured to a frame of the gas turbine engine and disposed radially inward of the fairing assembly;
a second component, disposed axially adjacent to the first component;
a flow diverter including a mounting portion securing the flow diverter to the first component, and an arm extending in an axial direction from the mounting portion toward the second component; and
a finger seal including a fixed end secured between the flow diverter mounting portion and the first component;
wherein the mounting portion includes a snap ring received by a recess on the first component, and a radial flange bolted to a radial surface of the first component; and
wherein the fixed end of the finger seal is bolted between the radial flange and the radial surface of the first component.

2. The assembly of claim 1 , wherein the second component is located downstream of the first component with respect to a direction of flow through the fairing assembly, and wherein the flow diverter directs a leakage gas flow from a rotor cavity away from the finger seal.

3. The assembly of claim 1 , wherein the flow diverter and the second component are arranged to form a gap therebetween for redirecting a secondary gas flow passing across the finger seal, along the second component.

4. The assembly of claim 1 , wherein the second component includes a gap for returning at least a portion of the secondary gas flow back to the main gas flow passage of the gas turbine engine.

5. A flow diverter assembly for a gas turbine engine, comprising:
a flow diverter element including a mounting portion and an arm extending generally axially from the mounting portion, the mounting portion including a snap ring for an interference fitting, and a seal backing ring;
a finger seal including a fixed end and a free end, the fixed end fastened to the backing ring;
a first gas turbine engine component, wherein the finger seal is fastened between the flow diverter backing ring and a radial surface of the first gas turbine engine component; and
a second gas turbine engine component disposed axially adjacent to the first gas turbine engine component, wherein a free end of the finger seal contacts a surface of a second gas turbine engine component disposed axially adjacent to the first gas turbine engine component;
wherein the second gas turbine engine component comprises a labyrinth seal.

6. The flow diverter assembly of claim 5 , wherein the first gas turbine engine component comprises a radially extending seal support ring.

7. The flow diverter assembly of claim 5 , wherein the arm is adapted to operate as a backup seal for the finger seal.

8. The flow diverter assembly of claim 5 , wherein the finger seal and the flow diverter are positioned in a rotor cavity radially inward of a main gas flow passage of the gas turbine engine for directing a secondary gas flow away from the rotor cavity and back toward the main gas flow passage.

9. The flow diverter assembly of claim 8 , wherein the secondary gas flow is routed around one or more components of the gas turbine engine.

10. A flow diverter for a gas turbine engine, the flow diverter comprising:
a mounting portion including a snap ring for an interference fitting, and a seal backing ring;
a flow diverter arm extending generally axially from a junction of the interference fitting and the backing ring; and
a first gas turbine engine component, wherein the snap ring is received by a recessed portion of the first gas turbine engine component; and
wherein the backing ring is a radial flange comprising a plurality of circumferentially distributed fastener holes for removably securing both the flow diverter and a fixed end of a finger seal to a first gas turbine engine component.

11. The flow diverter of claim 10 , wherein the first gas turbine engine component comprises a seal support disk.

Assignees

• United Technologies Corp

Inventors

• Vo Tuan David

Classifications

• F01D11/08 Primary

  for sealing space between rotor blade tips and stator (specially-shaped blade tips therefor F01D5/20) · CPC title

• F05D2260/6022

  of leakage having past a seal · CPC title

• F02C7/28 Primary

  Arrangement of seals · CPC title

• F05D2240/55

  Seals · CPC title

• F01D9/02

  Nozzles; Nozzle boxes; Stator blades; Guide conduits {, e.g. individual nozzles (nozzle boxes F01D9/047)} · CPC title