Aircraft propulsion system seal assembly with spring seal element and compliant seal element

Patent metadata

Field	Value
Publication number	US-10145256-B2
Application number	US-201715488935-A
Country	US
Kind code	B2
Filing date	Apr 17, 2017
Priority date	Apr 17, 2017
Publication date	Dec 4, 2018
Grant date	Dec 4, 2018

Abstract

An assembly is provided for an aircraft propulsion system. The assembly includes a first component, a second component and a seal assembly configured to seal a gap between the first and the second components. The seal assembly includes a metal spring seal element and an elastomeric seal element. The metal spring seal element is mounted to the first component. The metal spring seal element is sealingly engaged with the second component. The elastomeric seal element is mounted to the metal spring seal element. The elastomeric seal element is sealingly engaged with the second component.

First claim

We claim:

1. An assembly for an aircraft propulsion system, comprising:
a first component of the aircraft propulsion system;
a second component of the aircraft propulsion system; and
a seal assembly configured to seal a gap between the first component and the second component, the seal assembly including a metal spring seal element and an elastomeric seal element;
the metal spring seal element mounted to the first component, and sealingly engaged with the second component; and
the elastomeric seal element mounted to the metal spring seal element, and sealingly engaged with the second component;
wherein the elastomeric seal element comprises a tubular portion that elastically deforms when engaging the second component.

2. The assembly of claim 1 , wherein
a first portion of the metal spring seal element is mounted to the first component;
a second portion of the metal spring seal element is sealingly engaged with the second component; and
the elastomeric seal element is mounted to the first portion of the metal spring element.

3. The assembly of claim 2 , wherein the second portion of the metal spring element is cantilevered from the first portion of the metal spring element.

4. The assembly of claim 1 , wherein the metal spring element comprises a feathered spring element body.

5. The assembly of claim 4 , wherein
the metal spring element further comprises a second feather spring element body; and
slots in the feathered spring element body are offset from slots in the second feather spring element body.

6. The assembly of claim 1 , wherein
the metal spring element comprises a distal end portion with an arcuate sectional geometry; and
a convex surface of the distal end portion sealingly contacts the second component.

7. The assembly of claim 1 , wherein the seal assembly further includes a retainer mounting the elastomeric seal element to the metal spring element.

8. The assembly of claim 7 , wherein the retainer has a generally C-shaped sectional geometry.

9. The assembly of claim 1 , wherein the elastomeric seal element comprises a bulb seal element.

10. The assembly of claim 1 , wherein
the first component comprises an inner fixed structure of a nacelle for the aircraft propulsion system; and
the second component comprises a pylon structure for the aircraft propulsion system.

11. The assembly of claim 1 , further comprising a thermal insulator between the metal spring element and the elastomeric seal element.

12. The assembly of claim 1 , wherein the tubular portion is configured with a hollow inner bore.

13. An assembly for an aircraft propulsion system, comprising:
a first component of the aircraft propulsion system;
a second component of the aircraft propulsion system; and
a seal assembly configured to seal a gap defined by and extending between the first component and the second component, the seal assembly including a spring seal element and a bulb seal element with an unfilled inner bore;
the spring seal element attached to the first component, and sealingly contacting the second component; and
the bulb seal element attached to the spring seal element, and sealingly contacting the second component.

14. The assembly of claim 13 , wherein the spring seal element comprises metal.

15. The assembly of claim 13 , wherein the bulb seal element comprises elastomeric polymer.

16. The assembly of claim 13 , wherein the spring seal element is configured within the gap as a heat shield for the bulb seal element.

17. The assembly of claim 13 , wherein the spring seal element comprises a plurality of stacked feathered spring element bodies.

18. A seal assembly for sealing a gap formed by and extending between first and second components of an aircraft propulsion system, the seal assembly comprising a metal spring seal element and an elastomeric bulb seal element with a hollow inner bore, the metal spring seal element comprising a first portion and a second portion, the first portion configured to mount to the first component, the second portion configured to sealingly contact the second component, and the elastomeric bulb seal element mounted to the first portion and configured to sealing contact and be compressed against the second component, wherein the metal spring seal element is configured as a turkey feather seal element.

Assignees

• Rohr Inc

Inventors

• Ratajac Aleksandar
• Aten Michael

Classifications

• F02C7/28

  Arrangement of seals · CPC title

• F16J15/002

  comprising at least two sealings in succession (F16J15/162, F16J15/40 take precedence) · CPC title

• F05D2240/55

  Seals · CPC title

• F01D11/003 Primary

  by packing rings; Mechanical seals · CPC title

• F16J15/027

  and with a hollow profile · CPC title