Housing device for a compressor stage of a compressor device that is embodied with multiple stages and method for manufacturing a housing device

Patent metadata

Field	Value
Publication number	US-10119547-B2
Application number	US-201514960868-A
Country	US
Kind code	B2
Filing date	Dec 7, 2015
Priority date	Dec 29, 2014
Publication date	Nov 6, 2018
Grant date	Nov 6, 2018

Abstract

A housing device for a compressor stage of a compressor device of an aircraft engine that is embodied in a multi-stage design, including a flange area for connection to at least one housing device of another compressor stage that is adjacent in the axial direction. The housing device has a rotor area that during operation of the housing device directly acts together with the rotor blades of a rotor device in the radial direction of the compressor device. Further, the housing device has at least one reception area that is provided for receiving guide blades of a stator device. At least one part of the housing device is made of a sheet metal part. What is further described is a method for manufacturing such a housing device, with at least one part of the housing device being manufactured by means of a forming process.

First claim

The invention claimed is:

1. A housing device for a compressor stage of a multi-stage compressor device of an aircraft engine, comprising:
a flange area for connection to a further housing device of a further compressor stage that is adjacent to the compressor stage in an axial direction of the aircraft engine,
a rotor area that directly acts together with rotor blades of a rotor device of the compressor stage in a radial direction of the multi-stage compressor device during operation of the housing device, and
a reception area for receiving guide blades of a stator device,
wherein at least one chosen from the flange area, the rotor area and the reception area is made from sheet metal,
wherein a first sheet metal part of the housing device comprises the flange area, a second sheet metal part of the housing device comprises the rotor area and at least one third sheet metal part of the housing device comprises the reception area.

2. The housing device according to claim 1 , wherein at least two chosen from the flange area, the rotor area and the reception area is made from sheet metal, where the sheet metal of the of the different areas has different wall thicknesses.

3. The housing device according to claim 1 , wherein at least one chosen from the flange area, the rotor area and the reception area includes a bent sheet metal portion.

4. The housing device according to claim 1 , wherein the flange area includes a bend in an area of the connection to the further housing device.

5. The housing device according to claim 1 , wherein the flange area, the rotor area and the reception area are firmly bonded together.

6. The housing device according to claim 1 , wherein the rotor area includes an abrasive layer on a side that faces towards the rotor blades.

7. A method for manufacturing a housing device for a compressor stage of a multi-stage compressor device of an aircraft engine, comprising:
providing for the housing device:
a flange area for connection to a further housing device of a further compressor stage that is adjacent to the compressor stage in an axial direction of the aircraft engine,
a rotor area that directly acts together with rotor blades of a rotor device of the compressor stage in a radial direction of the multi-stage compressor device during operation of the housing device, and
a reception area for receiving guide blades of a stator device,

providing that at least one chosen from the flange area, the rotor area and the reception area is made from sheet metal;
providing that a first sheet metal part of the housing device comprises the flange area, a second sheet metal part of the housing device comprises the rotor area and at least one third sheet metal part of the housing device comprises the reception area;
providing that at least one chosen from the flange area, the rotor area and the reception area has been manufactured by a forming process.

8. The method according to claim 7 , wherein the forming process is a near-net shape forming process.

9. The method according to claim 7 , and further comprising:
manufacturing an intermediate cross-section of at least one chosen from the flange area, the rotor area and the reception area a flat base body,
subsequently converting the intermediate cross-section into a ring shape,
connecting end areas of the ring shape to each other or arranging the end areas at a distance from each other to provide a gap between the end areas.

10. The method according to claim 7 , and further comprising manufacturing the flange area, the rotor area and the reception area as separate components and subsequently connecting the flange area, the rotor area and the reception area to each other in a firmly bonded manner.

11. The method according to claim 7 , and further comprising submitting at least one chosen from the flange area, the rotor area and the reception area to post-processing.

12. A housing device for a compressor stage of a multi-stage compressor device of an aircraft engine, comprising:
a flange area for connection to a further housing device of a further compressor stage that is adjacent to the compressor stage in an axial direction of the aircraft engine,
a rotor area that directly acts together with rotor blades of a rotor device of the compressor stage in a radial direction of the multi-stage compressor device during operation of the housing device, and
a reception area for receiving guide blades of a stator device,
wherein at least one chosen from the flange area, the rotor area and the reception area is made from sheet metal;
wherein a first sheet metal part of the housing device comprises the flange area and the rotor area and a second sheet metal part of the housing device includes the reception area.

Assignees

• Rolls Royce Deutschland Ltd & Co Kg

Inventors

• Rautenstrauch Marco

Classifications

• F04D19/022 Primary

  with concentric rows of vanes; · CPC title

• F04D29/522

  especially adapted for elastic fluid pumps · CPC title

• F05D2230/54

  by sheet metal manufacturing · CPC title

• F01D25/246

  Fastening of diaphragms or stator-rings · CPC title

• F04D19/02

  Multi-stage pumps · CPC title