Assembly for a turbine engine

Patent metadata

Field	Value
Publication number	US-10934884-B2
Application number	US-201916369972-A
Country	US
Kind code	B2
Filing date	Mar 29, 2019
Priority date	Mar 30, 2018
Publication date	Mar 2, 2021
Grant date	Mar 2, 2021

Abstract

An assembly ( 50 ) for a turbine engine includes an annular row of stator blades with a longitudinal axis (B) having variable pitch blades each comprising a radial vane ( 6 ), at least one of its ends of which is connected to a radially extending pivot ( 14 ) and being engaged in rotation around its axis (A) in a ring ( 16 ), characterised in that a tubular component ( 26 ) is mounted coaxially around the pivot ( 14 ), wherein said tubular component ( 26 ) comprises a first annular zone ( 26 a ) mounted tightly on the pivot ( 14 ) and a second annular zone ( 26 b ) comprising an annular bulge ( 28 ) extending substantially radially outwards in relation to the axis (A) of the pivot ( 14 ), wherein the annular bulge ( 28 ) and the pivot ( 14 ) define an annular space ( 30 ).

First claim

The invention claimed is:

1. Assembly ( 50 ) for a turbine engine comprising an annular row of stator blades ( 2 ) with a longitudinal axis (B) having variable pitch blades ( 4 ) each comprising a radial vane ( 6 ), at least one of its ends of which is connected to a radially extending pivot ( 8 , 14 ) and being engaged in rotation around its axis (A) in a ring ( 16 ), characterised in that a tubular component ( 26 ) is mounted coaxially around the pivot ( 8 , 14 ), wherein said tubular component ( 26 ) comprises a first annular zone ( 26 a ) mounted tightly on the pivot ( 8 , 14 ) and a second annular zone ( 26 b ) comprising an annular bulge ( 28 ) extending substantially radially outwards in relation to the axis (A) of the pivot ( 8 , 14 ), wherein the annular bulge ( 28 ) and the pivot ( 8 , 14 ) define an annular space ( 30 ).

2. Assembly ( 50 ) according to claim 1 , characterised in that said tubular component ( 26 ) is mounted on the pivot ( 8 , 14 ) of the blade ( 4 ) such that the first annular zone ( 26 a ) is interposed along the axis (A) of said pivot ( 8 , 14 ) between the annular bulge ( 28 ) and a support plate ( 20 ) of the vane ( 6 ).

3. Assembly ( 50 ) according to claim 1 , characterised in that a third annular zone ( 26 c ) is formed on the tubular component ( 26 ) along the axis (A) of said pivot ( 8 , 14 ) such that the second annular zone ( 26 b ) is interposed between the first annular zone ( 26 a ) and the third annular zone ( 26 c ); wherein the third annular zone ( 26 c ) comprises an annular face ( 32 ) radially internal in relation to the axis (A) of the pivot ( 8 , 14 ) in contact with said pivot ( 8 , 14 ).

4. Assembly ( 50 ) according to claim 3 , characterised in that said annular face ( 32 ) is convex rounded shape.

5. Assembly ( 50 ) according to claim 1 , characterised in that the annular bulge ( 28 ) comprises a face that is radially internal ( 28 a ) in relation to the axis (A) of the pivot ( 8 , 14 ) which is concave and a face that is radially external ( 28 b ) in relation to the axis (A) of the pivot ( 8 , 14 ) which is convex.

6. Assembly ( 50 ) according to claim 1 , characterised in that the first zone ( 26 a ) is formed at a first end ( 34 ) of the tubular component ( 26 ).

7. Assembly ( 50 ) according to claim 3 , characterised in that the third annular zone ( 26 c ) is formed at a second end ( 36 ) of the tubular component ( 26 ).

8. Assembly ( 50 ) according to claim 1 , characterised in that said pivot ( 14 ) is formed at the end of the blade ( 4 ) that is radially internal in relation to the longitudinal axis (B).

9. Assembly ( 50 ) according to claim 1 , characterised in that the ring ( 16 ) comprises a plurality of housings ( 18 ), regularly distributed around the axis of the ring.

10. Assembly ( 50 ) according to claim 9 , characterised in that said tubular component is mounted coaxially around a pivot ( 8 , 14 ) and is accommodated in one of the housings ( 18 ), such that the radially external face ( 28 b ) of the annular bulge ( 28 ) is stressed radially towards the inside of the housing.

11. Assembly ( 50 ) according to claim 10 , characterised in that said plurality of housings ( 18 ) each respectively receives a bush ( 38 ) in which a tubular component ( 26 ) surrounding a pivot ( 14 ) is engaged.

12. Turbine engine comprising at least one assembly according to a compressor according to claim 10 .

13. Assembly ( 50 ) according to claim 9 , characterised in that said plurality of housings ( 18 ) each respectively receives a bush ( 38 ) in which a tubular component ( 26 ) surrounding a pivot ( 14 ) is engaged.

14. Turbine engine compressor characterised in that it comprises at least one assembly according to claim 1 .

15. Turbine engine comprising at least one assembly according to claim 1 .

16. A high-pressure compressor characterised in that it comprises at least one assembly according to claim 1 .

17. A turbojet or a turboprop comprising at least one assembly according to claim 1 .

Assignees

• Safran Aircraft Engines

Inventors

• Onfray Rémi Philippe Guy
• Frossard Benoit André Pierre
• Miraton Clément

Classifications

• F04D29/563

  specially adapted for elastic fluid pumps · CPC title

• F05D2250/711

  convex · CPC title

• F05D2250/241

  spherical · CPC title

• F05D2230/642

  using maintaining alignment while permitting differential dilatation · CPC title

• F05D2240/54

  Radial bearings · CPC title