# US 2018/0320631 A1 · Flow guiding device and method for forming a flow guiding device

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- Number: US 2018/0320631 A1
- Document ID: US20180320631A1
- Status: Published application
- Kind: A1
- Application number: 15/970,034
- Filed: 2018-05-03
- Published: 2018-11-08
- Earliest claimed: 2017-05-05
- Assignees: Rolls-Royce Deutschland Ltd & Co KG
- Applicants: Rolls-Royce Deutschland Ltd & Co KG
- Inventors: Igor SIKORSKI; Jason PHILLIPS
- Web page: https://patentgrep.com/patent/US20180320631A1

## CPC

- F02F 7/0082: {Mounting of engine casings}
- F01D 5/084: {the fluid circulating at the periphery of a multistage rotor, e.g. of drum type}
- F01D 25/12: Cooling
- F01D 25/243: {Flange connections; Bolting arrangements (F01D25/265 takes precedence)}
- F02C 7/18: the medium being gaseous, e.g. air {(F02C7/125 takes precedence)}
- F02F 7/0085: {Materials for constructing engines or their parts}
- F02F 7/0095: {Constructing engine casings (welded casings F02F7/0034)}
- F02C 3/00: Gas-turbine plants characterised by the use of combustion products as the working fluid (generated by intermittent combustion F02C5/00)
- Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft
- F02F: CYLINDERS, PISTONS OR CASINGS, FOR COMBUSTION ENGINES; ARRANGEMENTS OF SEALINGS IN COMBUSTION ENGINES
- F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D)
- F02C: GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines F01D; jet-propulsion plants F02K; construction of compressors or fans F04; generating combustion products of high pressure or high velocity F23R; using gas turbines in compression refrigeration plants F25B11/00)
- Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION

## Abstract

A flow guiding appliance of a turbomachine, in particular of an aircraft engine, for a partial exit flow of an outlet guide vane of a compressor, wherein, a flow guiding element delimits an annular channel about a shaft of the turbomachine. A frictional engagement connecting surface at the circumference of the flow guiding element connects the flow guiding element to another structural component of the turbomachine. The frictional engagement connecting surface with a closed enveloping surface can be inserted in a deformed state into the structural component with a circular cylindrical sealing surface with at least two opposite points. The at least two points of the closed enveloping surface are arranged in at least two opposite frictionally engaged contact areas of the circular cylindrical sealing surface following deformation. The invention also relates to a method for creating a flow guiding element.

## Claims

### Claim 1

A flow guiding appliance of a turbomachine, in particular of an aircraft engine, for a partial flow of the exit flow of an outlet guide wheel of a compressor, wherein, in the assembled state, a flow guiding element delimits an annular channel about a shaft of the turbomachine,
characterized by
a frictional engagement connecting surface at the circumference of the flow guiding element for connecting the flow guiding element to another structural component of the turbomachine, wherein the frictional engagement connecting surface with a closed enveloping surface can be inserted into the structural component with a circular cylindrical sealing surface in a deformed state with at least two opposite points, wherein, in the assembled state, the at least two points of the closed enveloping surface are arranged in at least two opposite frictionally engaged contact areas of the circular cylindrical sealing surface following deformation.

### Claim 2 (depends on 1)

The flow guiding appliance according to claim 1, wherein the closed enveloping surface has an elliptical cross section, a regular polygonal cross section, or an oval cross section.

### Claim 3 (depends on 2)

The flow guiding appliance according to claim 2, wherein the elliptical cross section of the closed enveloping surface has an eccentricity of between 0.95 and 0.999, in particular of between 0.99 and 0.996.

### Claim 4 (depends on 1)

The flow guiding appliance according to claim 1, wherein the contact points are positioned at the ends of the major axis of the closed enveloping surface with an elliptical cross section.

### Claim 5 (depends on 1)

The flow guiding appliance according to claim 1, wherein the frictional engagement connecting surface has a diameter tolerance of +/−0.3 mm.

### Claim 6 (depends on 1)

The flow guiding appliance according to claim 1, wherein the structural component with the circular cylindrical sealing surface has a diameter tolerance of +/−0.1 mm.

### Claim 7 (depends on 1)

The flow guiding appliance according to claim 1, wherein the annular channel at least partially has a substantially constant radial height, a convergent part, and/or a divergent part.

### Claim 8 (depends on 1)

The flow guiding appliance according to claim 1, wherein at least two gaps are present between the deformed enveloping surface and the circular cylindrical sealing surface following deformation of the flow guiding element with the closed enveloping surface when it is installed into the structural component.

### Claim 9 (depends on 8)

The flow guiding appliance according to claim 8, wherein two gaps are present between the deformed enveloping surface and the circular cylindrical sealing surface in an enveloping surface with an elliptical cross section following forming along the major axis of the ellipse.

### Claim 10 (depends on 9)

The flow guiding appliance according to claim 9, wherein the greatest radial width of the two gaps is less than 0.5 mm, in particular less than 0.3 mm, especially in particular less than 0.2 mm.

### Claim 11 (depends on 1)

The flow guiding appliance according to claim 1, wherein the flow guiding element is made of a nickel alloy, in particular of Inconel 718.

### Claim 12 (depends on 1)

A turbomachine, in particular an aircraft engine, with a flow guiding appliance according to claim 1.

### Claim 13 (depends on 12)

The turbomachine according to claim 12, wherein the flow guiding appliance extends axially from the outlet guide vane of a high-pressure compressor up to the central area of a combustion chamber.

### Claim 14 (depends on 1)

A method for creating a flow guiding appliance according to claim 1, wherein
a) a forming tool with a non-circular cross section is used for giving an at least partially non-circular cross section to a circular cylindrical molded body for the flow guiding element as a closed enveloping surface,
b) for connecting the flow guiding element to another structural component of the turbomachine, the flow guiding element has a frictional engagement connecting surface at the circumference, wherein the frictional engagement connecting surface with the closed enveloping surface is inserted in a deformed state into the structural component with a circular cylindrical sealing surface with at least two opposite points, so that, in the assembled state, the at least two points of the closed enveloping surface are arranged in at least two opposite frictionally engaged contact areas of the circular cylindrical sealing surface following deformation.