Aerodynamic link in part of a turbine engine

Patent metadata

Field	Value
Publication number	US-10689992-B2
Application number	US-201715626769-A
Country	US
Kind code	B2
Filing date	Jun 19, 2017
Priority date	Jun 20, 2016
Publication date	Jun 23, 2020
Grant date	Jun 23, 2020

Abstract

The invention relates to part of a turbine engine comprising two arms passing through a stream of the turbine engine, wherein each arm comprises an outer surface and an aerodynamic linking device. The aerodynamic linking device comprises fairings extending between the two arms, compressible interface means interposed between the fairings and means for retaining the fairings in place by pressure in relation to the arms, which compress the interface means.

First claim

The invention claimed is:

1. Part of a turbine engine, said part having an axis and comprising:
radially to said axis, an internal structural limit and an external structural limit which limit therebetween a stream of the turbine engine,
a first arm and a second arm, each passing through said stream of the turbine engine in which stream the first arm, which is structurally distinct from the second arm, is disposed upstream from the second arm, the first arm connecting together the internal structural limit and the external structural limit, and, separately from the first arm, the second arm connecting together the internal structural limit and the external structural limit, and
an aerodynamic linking device which comprises:
first and second fairings extending in the stream, between the first arm and the second arm,
first compressible interface means and second compressible interface means, the first compressible interface means being interposed between the first and second fairings and the first arm, and the second compressible interface means being interposed between the first and second fairings and the second arm, and
pressure retaining means for urging the first and second fairings towards each other which applies a pressure to the first and second arms, and which compress the first and second compressible interface means.

2. The part of a turbine engine of claim 1 , wherein the pressure retaining means comprises means for bringing the first and second fairings closer to each other.

3. The part of a turbine engine of claim 2 , wherein between the first and second arms arranged along said axis, the first and second fairings are separated from each other by a space having a width along which some at least of said first and second compressible interface means extend, such that bringing the first and second fairings closer to each other transversally to said axis, via said means for bringing the first and second fairings closer to each other, results in an axial abutment of the first and second compressible interface means against the first and second arms.

4. The part of a turbine engine of claim 1 , wherein the first and second compressible interface means are interposed between the fairings and outer surfaces of the arms.

5. The part of a turbine engine of claim 1 , wherein the first and second compressible interface means are made of elastically deformable material.

6. The part of a turbine engine of claim 5 , wherein the elastically deformable material is an elastomer.

7. The part of a turbine engine of claim 1 , wherein:
one of the first and second arms has a leading edge and a trailing edge and belongs to an intermediate casing of the turbine engine, thus extending radially between an internal hub and an external shroud, respectively corresponding to a first part of said internal and external structural limits and jointly delimiting a first part of said stream which is designed for passage of a secondary air flow in the turbine engine,
the other of the first and second arms has a leading edge and a trailing edge and extends between an internal casing and an external casing of the turbine engine respectively corresponding to a second part of said internal and external structural limits and jointly delimiting a second part of said stream, and
the second arm has a section larger than that of the first arm, and the first and second fairings run together flaring from the first arm to the second arm, jointly covering, at a first axial end, the trailing edge of the first arm and, at a second axial end, the leading edge of the second arm.

8. The part of a turbine engine of claim 1 , wherein the first arm connects an internal hub of the turbine engine and an external shroud of the turbine engine, and wherein the second arm connects an internal casing of the turbine engine and an external casing of the turbine engine.

9. A method for modifying an area between a first arm and a second arm in a stream of a turbine engine having an axis, the stream being limited, radially to said axis, by an internal structural limit and an external structural limit, wherein each of the first and second arms has an outer surface, the first arm connecting together the internal structural limit and the external structural limit, and, separately from the first arm, the second arm connecting together the internal structural limit and the external structural limit, and wherein the method comprises stages in which:
an aerodynamic linking device is used comprising first and second fairings, first and second compressible interface means and pressure retaining means for retaining the first and second fairings in place by pressure in relation to the first and second arms,
the first and second fairings are arranged so as to extend between the first and second arms, around a part of said outer surfaces, by interposing the first and second compressible interface means between the first and second fairings,
and through the pressure retaining means, a stress is applied to the first and second fairings, which stress retains the first and second fairings in place by pressure in relation to the first and second arms, by compressing the first and second compressible interface means.

10. Part of a turbine engine having an axis and comprising:
two arms passing through a stream of the turbine engine, each of said two arms comprising an outer surface, and
an aerodynamic linking device which comprises:
fairings extending in the stream, between the two arms;
compressible interface means interposed between the fairings; and
pressure retaining means for retaining the fairings in place by pressure in relation to the arms, which compress the compressible interface means, wherein:
a first of the two arms has a leading edge and a trailing edge and belongs to an intermediate casing of the turbine engine, thus extending radially between an internal hub and an external shroud jointly delimiting a first part of a secondary stream designed for passage of a secondary air flow, and,
a second of the two arms has a leading edge and a trailing edge and extends between an internal casing and an external casing of the turbine engine, jointly delimiting a second part of the secondary stream, the second arm having a section larger than that of the first arm, and the fairings running together flaring from the first arm to the second arm, jointly covering, at a first axial end, the trailing edge of the first arm and, at a second axial end, the leading edge of the second arm.

11. The part of claim 10 , wherein, in said stream, the first arm is structurally separate from the second arm and disposed upstream from the second arm, parallel to said axis.

Assignees

• Safran Aircraft Engines

Inventors

• Kohn Thierry
• Cesar Damien
• Sayn-Urpar Julien

Classifications

• F05D2260/37

  by a press fit connection · CPC title

• F04D29/644

  especially adapted for elastic fluid pumps · CPC title

• F04D29/542

  Bladed diffusers (fixing blades to stators F01D9/042) · CPC title

• F01D25/162

  Bearing supports · CPC title

• F05D2260/38

  by a spring, i.e. spring loaded or biased towards a certain position · CPC title