Coating for compressor outlet housing

Patent metadata

Field	Value
Publication number	US-11293451-B2
Application number	US-201916590450-A
Country	US
Kind code	B2
Filing date	Oct 2, 2019
Priority date	Oct 2, 2019
Publication date	Apr 5, 2022
Grant date	Apr 5, 2022

Abstract

A compressor outlet housing with a housing body has a volute and a radially inwardly extending wall extending from a radially inner surface of the volute. The radially inwardly extending wall extends inwardly to a ledge. A radially inwardly extending web extends to a bearing support. A fillet which will face an impeller when the compressor outlet housing is mounted in a compressor. The fillet connects the ledge to the web. An erosion resistant coating is formed on the fillet. In addition, a compressor incorporating the compressor housing is disclosed as is a method of repairing a compressor outlet housing.

First claim

The invention claimed is:

1. A compressor outlet housing comprising:
a housing body having a volute and a radially inwardly extending wall extending from a radially inner surface of said volute, and said radially inwardly extending wall extending inwardly to a ledge, a radially inwardly extending web extending to a bearing support, and a fillet which will face an impeller when said compressor outlet housing is mounted in a compressor, said fillet connecting said ledge to said web, and an erosion resistant coating being formed at least on said fillet; and
wherein a first radial distance is defined between a radially innermost surface of said ledge to a radially outermost surface of said bearing support, and measured perpendicular a central axis of said bearing support and a second radial distance is defined from a radially innermost end of said coating to said radially outermost surface of said bearing support also measured perpendicular to said central axis of said bearing support and a ratio of said first radial distance to said second radial distance is between 1.1 and 2.0.

2. The compressor outlet housing as set forth in claim 1 , wherein said erosion resistant coating is harder than an aluminum material forming said housing body.

3. The compressor outlet housing as set forth in claim 2 , wherein said erosion resistant coating is tungsten carbide.

4. The compressor outlet housing as set forth in claim 1 , wherein a third axial distance is defined between an axially forward end of said ledge to an axially forward end of said wall and a fourth axial distance being defined from an axially forward end of said coating to said axially forward end of said ledge along a line parallel to said central axis, and said ratio of said third axial distance to said fourth axial distance is between 1.1 and 2.0.

5. A compressor for use in an aircraft comprising:
a compressor impeller and a compressor inlet connected to supply air to said compressor impeller, said compressor inlet to be connected to a source of RAM air on an aircraft;
an electric motor for driving said compressor impeller, and a shaft driven by said electric motor to rotate said compressor impeller, said compressor impeller including seal teeth;
a compressor outlet housing with a housing body having a volute and a radially inwardly extending wall extending from a radially inner surface of said volute, and said radially inwardly extending wall extending inwardly to a ledge, a radially inwardly extending web extending to a bearing support, and a fillet facing said compressor impeller, said fillet connecting said ledge to said web, and an erosion resistant coating being formed at least on said fillet; and
wherein a first radial distance is defined between a radially innermost surface of said ledge to a radially outermost surface of said bearing support, and measured perpendicular to a central axis of said bearing support and a second radial distance is defined from a radially innermost end of said coaling to said radially outermost surface of said bearing support also measured perpendicular to said central axis of said bearing support and a ratio of said first radial distance to said second radial distance is between 1.1 and 2.0.

6. The compressor for use in an aircraft as set forth in claim 5 , wherein said erosion resistant coating is harder than an aluminum material forming said housing body.

7. The compressor for use in an aircraft as set forth in claim 6 , wherein said erosion resistant coating is tungsten carbide.

8. The compressor for use in an aircraft as set forth in claim 5 , wherein an outlet of said compressor outlet housing being connected to supply air to a cabin on an aircraft.

9. The compressor for use in an aircraft as set forth in claim 5 , wherein a third axial distance is defined between an axially forward end of said ledge to an axially forward end of said wall and a fourth axial distance being defined from an axially forward end of said coating to said axially forward end of said ledge measured along a line parallel to said central axis, and said ratio of said third axial distance to said fourth axial distance is between 1.1 and 2.0.

10. A method of repairing a compressor for use in an aircraft comprising the steps:
1) removing an existing compressor outlet housing from a compressor having a compressor impeller and a compressor inlet connected to supply air to said compressor impeller, said compressor inlet to be connected to a source of RAM air on an aircraft, an electric motor for driving said compressor impeller, and a shaft driven by said electric motor to rotate said compressor impeller, said compressor impeller including seal teeth; and
2) replacing the existing compressor outlet housing with a replacement compressor outlet housing, the replacement compressor outlet housing having a housing body with a volute and a radially inwardly extending wall extending from a radially inner surface of said volute, and said radially inwardly extending wall extending inwardly to a ledge, a radially inwardly extending web extending to a bearing support, and a fillet facing said compressor impeller, said fillet connecting said ledge to said web, and an erosion resistant coating being formed on said fillet; and
wherein a first radial distance is defined between a radially innermost surface of said ledge to a radially outermost surface of said bearing support, and measured perpendicular to a central axis of said bearing support and a second radial distance is defined from a radially innermost end of said coating to said radially outermost surface of said bearing support also measured perpendicular to said central axis of said bearing support and a ratio of said first radial distance to said second radial distance is between 1.1 and 2.0.

11. The method of repairing a compressor for use in an aircraft as set forth in claim 10 , wherein said erosion resistant coating is harder than an aluminum material forming said housing body.

12. The method of repairing a compressor for use in an aircraft as set forth in claim 11 , wherein said erosion resistant coating is tungsten carbide.

13. The method of repairing a compressor for use in an aircraft as set forth in claim 10 , wherein a third axial distance is defined between an axially forward end of said ledge to an axially forward end of said wall and a fourth axial distance being defined from an axially forward end of said coating to said axially forward end of said ledge measured along a line parallel to said central axis, and said ratio of said third axial distance to said fourth axial distance is between 1.1 and 2.0.

Assignees

• Hamilton Sundstrand Corp

Inventors

• Beers Craig M
• Rosen Seth E
• Merritt Brent J

Classifications

• C23C30/005

  on hard metal substrates · CPC title

• F05D2300/611

  Coating · CPC title

• F04D29/4206 Primary

  especially adapted for elastic fluid pumps · CPC title

• F04D29/289 Primary

  having provision against erosion or for dust-separation · CPC title

• F04D29/023

  especially adapted for elastic fluid pumps · CPC title