Large displacement high temperature seal

Patent metadata

Field	Value
Publication number	US-10378451-B2
Application number	US-201414913215-A
Country	US
Kind code	B2
Filing date	Sep 10, 2014
Priority date	Sep 13, 2013
Publication date	Aug 13, 2019
Grant date	Aug 13, 2019

Abstract

A seal assembly is provided for a gas turbine engine. This seal assembly includes a tadpole seal with a bulb and a tail, where the tail is directed toward a backwall. The seal assembly also includes a faying extension that at least partially extends into the channel and into contact with the bulb. An exhaust duct is also provided for a gas turbine engine. This exhaust duct includes a seal assembly between a first exhaust duct section and a second exhaust duct section. The seal assembly includes a tadpole seal with a bulb and a tail, where the tail is directed upstream.

First claim

What is claimed is:

1. An exhaust duct for a gas turbine engine, comprising:
a first exhaust duct section;
a second exhaust duct section adjacent to the first exhaust duct section;
a seal assembly between the first exhaust duct section and the second exhaust duct section, wherein the seal assembly includes a tadpole seal with a bulb and a tail, and the tail is directed upstream;
wherein the bulb is configured to translate axially when compressed by movement of a component of the seal assembly; and
a channel mounted to the first exhaust duct section, wherein the tadpole seal is located within the channel;
wherein the tail extends toward a backwall of the channel;
wherein the component of the seal assembly comprises a faying extension that at least partially extends axially into the channel and into axial contact with the bulb; and
wherein the component of the seal assembly comprises a faying extension that at least partially extends axially into the channel and into axial contact with the bulb.

2. The exhaust duct as recited in claim 1 , wherein the channel defines at least one port upstream of the bulb.

3. The exhaust duct as recited in claim 1 , wherein the tadpole seal defines a ring.

4. The exhaust duct as recited in claim 1 , wherein the tadpole seal includes laser cut end sections.

5. The exhaust duct of claim 1 , wherein the tadpole seal comprises a silica cover wrapped around an Inconel mesh bulb core.

6. An exhaust duct for a gas turbine engine, comprising:
a first exhaust duct section;
a second exhaust duct section adjacent to the first exhaust duct section; and
a seal assembly between the first exhaust duct section and the second exhaust duct section, the seal assembly comprising a tadpole seal and a faying extension attached to the second exhaust duct section;
the tadpole seal comprising a bulb and a tail that is directed upstream;
the faying extension projecting upstream to a distal end that axially engages the bulb, wherein the bulb is axially between the faying extension and the tail.

7. The exhaust duct of claim 6 , wherein the seal assembly further comprises a channel mounted to the first exhaust duct section, and the tadpole seal is located within the channel.

8. The exhaust duct of claim 7 , wherein the tail extends toward a backwall of the channel.

9. The exhaust duct of claim 8 , wherein the faying extension extends at least partially axially into the channel.

10. The exhaust duct of claim 9 , wherein the channel is configured with a port upstream of the bulb.

11. The exhaust duct of claim 6 , wherein the tadpole seal defines a ring.

12. The exhaust duct of claim 6 , wherein the tadpole seal includes laser cut end sections.

13. The exhaust duct of claim 6 , wherein the tadpole seal comprises a silica cover wrapped around a metal mesh core.

14. The exhaust duct of claim 6 , wherein the tadpole seal comprises a cover wrapped around a mesh core.

Assignees

• United Technologies Corp

Inventors

• Dillard Gary J

Classifications

• F05D2250/14

  elliptical · CPC title

• F16J15/06

  with solid packing compressed between sealing surfaces · CPC title

• F02K1/805 Primary

  Sealing devices therefor, e.g. for movable parts of jet pipes or nozzle flaps · CPC title

• F16J15/021

  with elastic packing (F16J15/08 takes precedence) · CPC title

• Y02T50/671

  Cross-Sectional Technologies · mapped topic