Compressor comprising a stator vane assembly having an inner ring and a seal carrier secured thereto with a clamping element

Patent metadata

Field	Value
Publication number	US-9624833-B2
Application number	US-201313784192-A
Country	US
Kind code	B2
Filing date	Mar 4, 2013
Priority date	Mar 5, 2012
Publication date	Apr 18, 2017
Grant date	Apr 18, 2017

Abstract

A compressor having a stator vane assembly having an inner ring and a seal carrier secured thereto, the seal carrier having two opposite seal carrier end faces and the inner ring having two inner ring end faces which face said seal carrier end faces and are received between said seal carrier end faces with an axial gap therebetween, at least one clamping element bearing axially with a first clamping element end face against the inner ring and with a second clamping element end face against the seal carrier and being axially resiliently clamped between the inner ring and the seal carrier. A compressor with a clamping element for radial clamping is also provided.

First claim

What is claimed is:

1. A compressor comprising:
a stator vane assembly having an inner ring and a seal carrier secured thereto, the seal carrier having two opposite seal carrier end faces and the inner ring having two inner ring end faces which face said seal carrier end faces and are received between said seal carrier end faces with an axial gap therebetween, and
at least one clamping element which bears axially with a first clamping element end face against the inner ring and with a second clamping element end face against the seal carrier and which is axially resiliently clamped between the inner ring and the seal carrier.

2. The compressor as recited in claim 1 wherein at least one of the first and second clamping element end faces has an entry ramp against the axial direction.

3. The compressor as recited in claim 1 wherein the clamping element is partially received within a recess in an inner ring end face and/or an inner ring peripheral surface.

4. The compressor as recited in claim 1 wherein the seal carrier is secured to the inner ring in a position that is rotated with respect to the mounting position; and a seal carrier end face has a through-hole for insertion of the clamping element into the recess which, in the mounting position, is in alignment with the through-hole.

5. The compressor as recited in claim 1 wherein the clamping element has a shoulder.

6. The compressor as recited in claim 1 wherein the clamping element has a circular or rectangular cross section.

7. An aircraft engine comprising the compressor as recited in claim 1 .

8. A compressor as recited in claim 1 comprising:
the seal carrier having two opposite seal carrier peripheral surfaces and the inner ring having two inner ring peripheral surfaces which face said seal carrier peripheral surfaces; ones of the seal carrier peripheral surfaces and of the inner ring peripheral surfaces being received between the other ones of the seal carrier peripheral surfaces and of the inner ring peripheral surfaces with a radial gap therebetween; and
wherein the at least one clamping element bears radially with a first clamping element peripheral surface against the inner ring and with a second clamping element peripheral surface against the seal carrier and which is radially resiliently clamped between the inner ring and the seal carrier.

9. A compressor comprising:
a stator vane assembly having an inner ring and a seal carrier secured thereto, the seal carrier having two opposite seal carrier peripheral surfaces and the inner ring having two inner ring peripheral surfaces which face said seal carrier peripheral surfaces; ones of the seal carrier peripheral surfaces and of the inner ring peripheral surfaces being received between the other ones of the seal carrier peripheral surfaces and of the inner ring peripheral surfaces with a radial gap therebetween; and
at least one clamping element which bears radially with a first clamping element peripheral surface against the inner ring and with a second clamping element peripheral surface against the seal carrier and which is radially resiliently clamped between the inner ring and the seal carrier.

10. The compressor as recited in claim 9 wherein at least one of the first and second clamping element peripheral surfaces has an entry ramp against the radial direction.

11. The compressor as recited in claim 9 wherein the clamping element is partially received within a recess in an inner ring end face and/or an inner ring peripheral surface.

12. The compressor as recited in claim 9 wherein the seal carrier is secured to the inner ring in a position that is rotated with respect to the mounting position; and a seal carrier end face has a through-hole for insertion of the clamping element into the recess which, in the mounting position, is in alignment with the through-hole.

13. The compressor as recited in claim 9 wherein the clamping element has a shoulder.

14. The compressor as recited in claim 9 wherein the clamping element has a circular or rectangular cross section.

15. An aircraft engine comprising the compressor as recited in claim 9 .

16. A method for securing the seal carrier to the inner ring of a compressor as recited in claim 1 wherein the clamping element is resiliently clamped between the seal carrier and the inner ring.

17. The method as recited in claim 16 wherein in a mounting position, the clamping element is partially inserted into a recess of an inner ring end face through a through-hole in a seal carrier end face, whereupon the seal carrier and the inner ring are rotated relative to each other and secured to each other, thereby resiliently clamping the clamping element between the seal carrier and the inner ring.

18. A method for securing the seal carrier to the inner ring of a compressor as recited in claim 9 wherein the clamping element is resiliently clamped between the seal carrier and the inner ring.

19. The method as recited in claim 18 wherein in a mounting position, the clamping element is partially inserted into a recess of an inner ring end face through a through-hole in a seal carrier end face, whereupon the seal carrier and the inner ring are rotated relative to each other and secured to each other, thereby resiliently clamping the clamping element between the seal carrier and the inner ring.

20. An inner ring for a compressor as recited in claim 1 .

21. An inner ring for a compressor as recited in claim 9 .

22. A seal carrier for a compressor as recited in claim 1 .

23. A seal carrier for a compressor as recited in claim 9 .

24. A clamping element for a compressor as recited in claim 1 .

25. A clamping element for a compressor as recited in claim 9 .

Assignees

• Mtu Aero Engines Gmbh

Inventors

• Kraus Juergen
• Kern Felix

Classifications

• F01D11/001

  for sealing space between stator blade and rotor · CPC title

• F02C7/28 Primary

  Arrangement of seals · CPC title

• F01D9/04 Primary

  forming ring or sector · CPC title