IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0968818
(2010-12-15)
|
등록번호 |
US-8708649
(2014-04-29)
|
우선권정보 |
EP-09015844 (2009-12-22) |
발명자
/ 주소 |
- Wery, Xavier
- Derclaye, Alain
- Penalver Castro, Enrique
|
출원인 / 주소 |
|
대리인 / 주소 |
Reinhart Boerner Van Deuren P.C.
|
인용정보 |
피인용 횟수 :
0 인용 특허 :
10 |
초록
▼
The present invention relates to a turbine engine rectifier stage comprising a plurality of fixed vanes connecting an inner ferrule support 19 to an outer ferrule support 14, said inner ferrule support and said outer ferrule support defining an aerodynamic vein and comprising a set of contiguously a
The present invention relates to a turbine engine rectifier stage comprising a plurality of fixed vanes connecting an inner ferrule support 19 to an outer ferrule support 14, said inner ferrule support and said outer ferrule support defining an aerodynamic vein and comprising a set of contiguously assembled sectors 20,15 respectively, the plurality of fixed vanes comprising so-called structural vanes 5 surrounding so-called non-structural or aero vanes 6 so as to form boxes 7, said structural vanes 5 being rigidly attached to the ends of the sectors of the inner ferrule support 20 by means of attachment elements 17 in order to impart increased stiffness to the boxes 7.
대표청구항
▼
1. A turbine-engine rectifier stage comprising a plurality of fixed vanes connecting an inner ferrule support (19) to an outer ferrule support (14), said inner ferrule support and said outer ferrule support defining an aerodynamic vein and comprising a set of contiguously assembled sectors (20,15),
1. A turbine-engine rectifier stage comprising a plurality of fixed vanes connecting an inner ferrule support (19) to an outer ferrule support (14), said inner ferrule support and said outer ferrule support defining an aerodynamic vein and comprising a set of contiguously assembled sectors (20,15), respectively, the plurality of fixed vanes comprising so-called structural vanes (5) surrounding so-called non-structural or aero vanes (6) so as to form boxes (7), said structural vanes (5) being rigidly attached to the ends of the sectors (20) of the inner ferrule support by means of attachment elements (17) in order to impart increased stiffness to the boxes (7); and wherein each sector of the outer ferrule support (15) comprises a zone (23) of reduced thickness at each of its ends, said zone forming with the zone (23) of the sector positioned side by side, a housing for a platform (9) of each structural vane at a blade head of each structural vane, said housing being of dimensions that are substantially equal to the dimensions of the platform (9) of each structural vane at the blade head of each structural vane and being positioned in the aerodynamic vein. 2. The rectifier stage as in claim 1, wherein each structural vane (5) comprises the platform (9) of each structural vane at the blade head of each structural vane and a platform (10) at a blade foot of each structural vane, said platforms (9,10) of each structural vane comprising holes for passage of attachment elements (17) and ensuring stiff attachment, once they are assembled to the sectors (20,15) of the respective inner ferrule supports and outer ferrule supports. 3. The rectifier stage as in claim 2, wherein each aero vane (6) comprises a foot (11) of each aero vane located in the alignment of a plane of a blade (12) of each aero vane and a bulb (13) or platform of each aero vane, located at a head of the blade of each aero vane, said platform of each aero vane being flat and normal to the plane of the blade of each aero vane. 4. The rectifier stage as in claim 3, wherein each sector (15) of the outer ferrule support comprises holes (16) intended to receive the bulb (13) or the platform of the aero vanes, and holes for the passage of attachment elements (17). 5. The rectifier stage as in claim 4, wherein the sectors (15) of the outer ferrule support are attached to a casing (3) comprising holes for the passage of attachment elements (17), and wherein the platforms (9) at the blade head of the structural vanes are attached together to the sectors (15) of the outer ferrule support and to the casing (3). 6. The rectifier stage as in claim 5, wherein the bulb (13) comprises two tilted supporting faces intended to be placed as an interface with the sector (15) of the outer ferrule support as well as a third supporting face that is perpendicular to the plane of the blade (12) intended to be placed as an interface with the casing (3). 7. The rectifier stage as in claim 5, wherein the casing (3) is made of a composite or metal material. 8. The rectifier stage as in claim 4, wherein the attachment elements (17) are positioned in metal nozzles (18) at the level of said holes. 9. The rectifier stage as in claim 4, wherein the attachment elements (17) comprise lock-bolts. 10. The rectifier stage as in claim 3, wherein each sector (20) of the inner ferrule support comprises piercings (21) intended to receive the feet (11) of the aero vanes as well as holes intended to receive the attachment elements (17) ensuring the assembling of the platforms (10) at the foot of the structural vanes with the sectors (20) of the inner ferrule support. 11. The rectifier stage as in claim 10, wherein an elastomeric joint (22) fills the gap between the foot (11) of the aero vane and the piercing (21). 12. The rectifier stage as in claim 1, wherein the structural vanes (5) are made of a more rigid material than the aero vanes (6). 13. The rectifier stage as in claim 12, wherein the structural vanes (5) and the aero vanes (6) are made of a metal and composite material, respectively. 14. The rectifier stage as in claim 1, wherein the inner ferrule support (19) and the outer ferrule support (14) are made of composite material. 15. The rectifier stage as in claim 1, wherein the structural vanes (5) have a thicker profile than the aero vanes (6). 16. Turbine engine compressor comprising a plurality of rectifier stages as in claim 1. 17. The compressor as in claim 16 comprising a half-shell casing (3) that integrates several rectifier stages. 18. A turbine-engine rectifier stage comprising a plurality of fixed vanes connecting an inner ferrule support (19) to an outer ferrule support (14), said inner ferrule support and said outer ferrule support defining an aerodynamic vein and comprising a set of contiguously assembled sectors (20,15), respectively, the plurality of fixed vanes comprising so-called structural vanes (5) surrounding so-called non-structural or aero vanes (6) so as to form boxes (7), said structural vanes (5) being rigidly attached to ends of the sectors (20) of the inner ferrule support by means of attachment elements (17) in order to impart increased stiffness to the boxes (7); and wherein each sector (20) of the inner ferrule support comprises a zone (23) of reduced thickness at each of its ends, said zone forming with the zone (23) of the sector positioned side by side, a housing for platform (10) of each structural vane at a blade foot of each structural vane, said housing being of dimensions that are substantially equal to the dimensions of the platform (10) of each structural vane at the blade foot of each structural vane and being positioned outside the aerodynamic vein.
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