Flexible seal for gas turbine engine system

Patent metadata

Field	Value
Publication number	US-9228533-B2
Application number	US-94781407-A
Country	US
Kind code	B2
Filing date	Nov 30, 2007
Priority date	Nov 30, 2007
Publication date	Jan 5, 2016
Grant date	Jan 5, 2016

Abstract

A gas turbine engine system includes an airframe support, a gas turbine engine mounted to the airframe support, a nozzle exhaust mounted to the airframe support, and a flexible annular seal having a first end that is attached to the gas turbine engine and a second end that is attached to an exhaust nozzle. The flexible annular seal may include a flexible annular wall that permits relative deflection between the gas turbine engine and the exhaust nozzle to facilitate the reduction of undesirable load transfer.

First claim

What is claimed is:

1. A flexible seal for use in a gas turbine engine system, comprising:
a flexible annular wall having a first end that is attachable to a gas turbine engine and a second end that is attachable to a nozzle exhaust, wherein the flexible annular wall comprises a first corrugate section including a first flange and a second corrugate section including a second flange mechanically secured against the first flange;
wherein the flexible annular wall comprises an elastomer composite having reinforcement fibers disposed within an elastomer matrix;
wherein the reinforcement fibers comprise glass fibers and the elastomer matrix comprises silicone.

2. A flexible seal for use in a gas turbine engine system, comprising:
a flexible annular wall having a first end that is attachable to a gas turbine engine and a second end that is attachable to a nozzle exhaust, wherein the flexible annular wall comprises a first corrugate section including a first flange and a second corrugate section including a second flange mechanically secured against the first flange;
wherein each of the first end and the second end comprises a flange for attachment;
wherein at least one of the flanges of the first end or second end comprises for receiving fasteners; and
a Marmon clamp secured to the flanges of the first end and second end using the fasteners.

3. A flexible seal for use in a gas turbine engine system, comprising:
a flexible annular wall having a first end that is attachable to a gas turbine engine and a second end that is attachable to a nozzle exhaust, wherein the flexible annular wall comprises a first corrugate section, a second corrugate section and a flexible central section joining the first corrugate section and the second corrugate section,
wherein the flexible central section has a lower degree of flexibility than the first corrugate section and the second corrugated section.

4. A flexible seal for use in a gas turbine engine system, comprising:
a flexible annular wall having a first end that is attachable to a gas turbine engine and a second end that is attachable to a nozzle exhaust, wherein the flexible annular wall comprises a first corrugate section, a second corrugate section and a flexible central section joining the first corrugate section and the second corrugate section,
wherein the flexible annular wall includes a reinforcement member within the flexible central section such that the flexible central section has a greater stiffness than the first corrugate section and the second corrugate section.

Assignees

• Roberts Steven D
• Monahan Richard W
• Pimenta David C
• United Technologies Corp

Inventors

• Roberts Steven D
• Monahan Richard W
• Pimenta David C

Classifications

• Y10T29/49297

  Seal or packing making · CPC title

• Y02T50/672

  Cross-Sectional Technologies · mapped topic

• F05D2300/431

  Rubber · CPC title

• F02C7/28

  Arrangement of seals · CPC title

• F05D2300/603

  Composites; e.g. fibre-reinforced · CPC title