Flow diverter element and assembly
AssigneeUnited Technologies Corporation
InventorTuan David Vo
Life of this patent
Estimating the term…
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.
Claims11
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.
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.
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.
Dependencies are inferred from the claim text.