Turbo-engine housing, equipped with a thermal protection shell and an anti-wear strip

Patent metadata

Field	Value
Publication number	US-10858954-B2
Application number	US-201816163814-A
Country	US
Kind code	B2
Filing date	Oct 18, 2018
Priority date	Oct 20, 2017
Publication date	Dec 8, 2020
Grant date	Dec 8, 2020

Abstract

A turbo-engine module comprises a turbo-engine housing, and a thermal protection shell of the housing. The thermal protection shell is configured to cover at least partially the housing in order to protect same thermally. The module comprises a wear protection strip which is situated between the housing and the thermal protection shell, in a junction region of the housing and the thermal protection shell.

First claim

The invention claimed is:

1. A turbo-engine module, comprising:
a turbo-engine housing,
a thermal protection shell of the housing, wherein the thermal protection shell is configured to cover at least partially the housing in order to protect the housing thermally,
wherein the module comprises a wear protection strip which is situated between the housing and the thermal protection shell in a junction region of the housing and the thermal protection shell,
wherein the wear protection strip comprises at least one recess, wherein the wear protection strip is open-worked at the recess,
wherein the recess is situated outside a zone for fastening the wear protection strip to the thermal protection shell and/or the housing.

2. The turbo-engine module according to claim 1 , wherein the wear protection strip covers a housing portion, wherein a material of the wear protection strip is the same as a material of the housing portion, and/or wherein a material of the wear protection strip is the same as a material of the thermal protection shell.

3. The turbo-engine module according to claim 1 , wherein the wear protection strip has a thickness between 0.3 mm and 0.8 mm.

4. The turbo-engine module according to claim 1 , wherein the thermal protection shell is secured to the housing by at least one attachment,
wherein the wear protection strip is fastened to the housing and to the thermal protection shell by the attachment.

5. The turbo-engine module according to claim 4 , wherein the attachment comprises a fastening screw.

6. The turbo-engine module according to claim 1 , wherein the wear protection strip is pressed by the thermal protection shell against the housing, wherein the wear protection strip conforms to the shape of the housing portion covered thereby.

7. The turbo-engine module according to claim 1 , wherein the thermal protection shell is centred with respect to the wear protection strip along a longitudinal direction of the module, wherein the wear protection strip is of greater width than the width of the thermal protection shell along the longitudinal direction of the module.

8. The turbo-engine module according to claim 1 , wherein the wear protection strip comprises:
a first circumferential segment configured to be placed in a first bearing zone of the thermal protection shell against the housing,
a second circumferential segment which is axially spaced with respect to the first circumferential segment and wherein the second circumferential segment is configured to be placed in a second bearing zone of the thermal protection shell against the housing, and
a connection zone between the circumferential segments, wherein the connection zone connects the first circumferential segment to the second circumferential segment,
wherein the connection zone is the zone for fastening the wear protection strip to the thermal protection shell and/or the housing.

9. The turbo-engine module according to claim 8 , wherein the housing comprises an annular boss which is situated axially between the first circumferential segment and the second circumferential segment, and wherein the annular boss forms an axial abutment for the first circumferential segment and the second circumferential segment.

10. The turbo-engine module according to claim 8 , wherein the recess is situated axially between the first bearing zone of the thermal protection shell against the housing and the second bearing zone of the thermal protection shell against the housing.

11. The turbo-engine module according to claim 1 , wherein the wear protection strip comprises a first annular sector and a second annular sector which is adjacent to the first annular sector along a circumferential direction of the module.

12. The turbo-engine module according to claim 1 , wherein the module comprises a turbo-engine compressor.

13. The turbo-engine module according to claim 12 , wherein the compressor is a high-pressure turbo-engine compressor.

14. The turbo-engine module according to claim 1 , wherein the housing is situated radially outside a gas flow jet in the turbo-engine relative to a longitudinal axis of the module, wherein the housing is traversed by orifices for extracting air in the jet.

15. The turbo-engine module according to claim 14 , wherein the housing comprises:
a first portion in a first material, and
a second portion which is adjacent to the first portion along the longitudinal axis of the module oriented in the gas flow direction through the module, wherein the second portion is made of a second material having a lower thermal expansion coefficient than the thermal expansion coefficient of the first material.

Assignees

• Safran Aircraft Engines

Inventors

• Bazot Olivier
• Edynak Jérémy Philippe Pierre
• Hussain Farhana
• Libes Fanny Marie

Classifications

• F01D25/145 Primary

  Thermally insulated casings · CPC title

• F05D2220/3219

  for the last stage of a compressor or a high pressure compressor · CPC title

• F05D2300/17

  Alloys · CPC title

• F01D25/246

  Fastening of diaphragms or stator-rings · CPC title

• F05D2240/15

  Heat shield · CPC title