Assembly for a turbomachine comprising a distributor, a structural element of the turbomachine, and an attachment device

Patent metadata

Field	Value
Publication number	US-10941668-B2
Application number	US-201716300153-A
Country	US
Kind code	B2
Filing date	May 5, 2017
Priority date	May 9, 2016
Publication date	Mar 9, 2021
Grant date	Mar 9, 2021

Abstract

Assembly (2) comprising an annular turbine distributor (3) for turbomachinery (1), an annular structural element (4) of the turbomachinery (1), coaxial with the distributor (3) and at least one device (5) for attaching the annular distributor (3) with the annular structural element (4), characterised in that: —the annular distributor (3) is crossed by at least two axial passages, and —the or each attachment device (5) comprises: at least two pins (15), rigidly connected to the annular structural element (4) and passing through one of said passages of the distributor (3), a first transverse stop (16) for stopping the distributor (3) axially and passing through two consecutive pins (15), and two second stops (17) rigidly connected to the structural element (4) to retain, in the pins (15), the first transverse stop (16) for stopping the distributor (3) radially.

First claim

The invention claimed is:

1. An assembly ( 2 ) comprising an annular turbine distributor ( 3 ) for turbomachinery ( 1 ), an annular structural element ( 4 ) of the turbomachinery ( 1 ), coaxial with the annular turbine distributor ( 3 ) and at least one attachment device ( 5 ) for attaching the annular turbine distributor ( 3 ) with the annular structural element ( 4 ), characterized in that:
the annular turbine distributor ( 3 ) is crossed by at least two axial passages ( 13 ), and
the at least one attachment device ( 5 ) comprises:
at least two pins ( 15 ) which are secured to the annular structural element ( 4 ) and passing through one of said at least two axial passages ( 13 ) of the annular turbine distributor ( 3 ), with each of said at least two pins ( 15 ) being further crossed by an opening ( 18 ),
a first transverse stop ( 16 ) for stopping the annular turbine distributor ( 3 ) axially and passing through the openings ( 18 ) of the at least two pins ( 15 ), where the at least two pins ( 15 ) are consecutive, and
two second stops ( 17 ) for retaining the first transverse stop ( 16 ) which are secured to the annular structural element ( 4 ) to retain the first transverse stop ( 16 ) in the openings ( 18 ) of the at least two pins ( 15 ).

2. The assembly ( 2 ) according to claim 1 , wherein the annular structural element ( 4 ) has at least one first hole ( 8 ) and at least one second hole ( 9 ).

3. The assembly ( 2 ) according to claim 2 , wherein the annular turbine distributor ( 3 ) comprises at least two tabs ( 12 ) positioned circumferentially away from one another and each having one of said at least two axial passages ( 13 ) adapted to come opposite said at least one first hole ( 8 ) of the annular structural element ( 4 ).

4. The assembly ( 2 ) according to claim 2 , wherein the at least two pins ( 15 ) are movable relative to the annular structural element ( 4 ) and each pass through said at least one first hole ( 8 ).

5. The assembly ( 2 ) according to claim 2 , wherein the two second stops ( 17 ) are adapted for circumferentially retaining the first transverse stop ( 16 ) are each accommodated in one said second hole ( 9 ).

6. The assembly ( 2 ) according to claim 2 , wherein the annular structural element ( 4 ) has, on a radially external edge ( 6 ), at least two lugs ( 7 ) positioned circumferentially away from one another and each provided with said at least one first ( 8 ) and second holes ( 9 ).

7. The assembly ( 2 ) according to claim 1 , wherein each of the two second stops ( 17 ) is movable relative to the annular structural element ( 4 ) and is accommodated in a space ( 14 ) of the annular turbine distributor ( 3 ).

8. The assembly ( 2 ) according to claim 1 , wherein the annular turbine distributor ( 3 ) comprises a plurality of circumferentially adjacent sectors ( 3 a ), with each sector ( 3 a ) having at least two of said at least two axial passages ( 13 ) and at least a portion of a space ( 14 ).

9. The assembly ( 2 ) according to claim 1 , wherein at least one of said at least two axial passages ( 13 ) of the annular turbine distributor ( 3 ) has a diameter greater than a diameter of at least one of the at least two pins ( 15 ) to ensure an accurate positioning of the annular turbine distributor ( 3 ).

10. The assembly ( 2 ) according to claim 1 , wherein the at least two pins ( 15 ) are respective circumferential stops of the annular turbine distributor.

11. Turbomachinery ( 1 ) comprising the assembly ( 2 ) according to claim 1 .

12. A method for assembling the assembly ( 2 ) according to claim 1 , wherein the at least one attachment device ( 5 ) comprises at least a first attachment device ( 5 ) and an, adjacent second attachment device ( 5 ) sharing one of the two second stops ( 17 ), with the method comprising the following steps:
positioning the at least two pins ( 15 ) of the first attachment device ( 5 ) on the annular structural element ( 4 );
positioning the two second stops ( 17 ) of the first attachment device ( 5 ) in a retracted position;
inserting the first transverse stop ( 16 ) of the first attachment device ( 5 ) through the openings ( 18 ) of the at least two pins ( 15 ) of the first attachment device ( 5 );
shifting the first transverse stop ( 16 ) of the first attachment device ( 5 ) in a direction opposite the second attachment device ( 5 );
positioning the at least two pins ( 15 ) of the second attachment device ( 5 ) on the annular structural element ( 4 );
inserting the first transverse stop ( 16 ) of the second attachment device ( 5 ) through the openings ( 18 ) of the at least two pins ( 15 ) of the second attachment device ( 5 );
positioning the two second stops ( 17 ) of the two attachment devices ( 5 ) in a locking position, with one of the two second stops ( 17 ) then locking the first transverse stops ( 16 ) of the two attachment devices ( 5 ).

13. The method according to claim 12 , wherein the step of positioning the at least two pins ( 15 ) of the first attachment device ( 5 ) and the second attachment device ( 5 ) on the annular structural element ( 4 ) is carried out prior to the positioning of the first stop ( 16 ) of the first attachment device ( 5 ) and the second attachment device ( 5 ) respectively.

Assignees

• Safran Aircraft Engines

Inventors

• Thomas Axel Sylvain Loïc
• Judet Maurice Guy
• Radeljak Gabrijel

Classifications

• F01D9/042 Primary

  fixing blades to stators (fixing stator-rings in the casing or to each other F01D25/246) · CPC title

• F05D2230/64

  using positioning or alignment devices for aligning or centring, e.g. pins · CPC title

• F01D25/246

  Fastening of diaphragms or stator-rings · CPC title

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title