IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0179980
(2014-02-13)
|
등록번호 |
US-10077719
(2018-09-18)
|
우선권정보 |
DE-10 2013 202 786 (2013-02-20) |
발명자
/ 주소 |
- Mojem, Mats
- Scholz, Andreas
|
출원인 / 주소 |
- Rolls-Royce Deutschland Ltd & Co KG
|
대리인 / 주소 |
Shuttleworth & Ingersoll, PLC
|
인용정보 |
피인용 횟수 :
0 인용 특허 :
9 |
초록
▼
A device for bleeding compressor air in a turbofan engine includes a low-pressure compressor of a primary duct, a fan stator arranged in a secondary duct downstream of a fan, and an arrangement for discharging compressor air from the low-pressure compressor into the secondary duct. The arrangement i
A device for bleeding compressor air in a turbofan engine includes a low-pressure compressor of a primary duct, a fan stator arranged in a secondary duct downstream of a fan, and an arrangement for discharging compressor air from the low-pressure compressor into the secondary duct. The arrangement includes air guiding devices to guide compressor air into the secondary duct upstream of the fan stator relative to the flow direction in the secondary duct, past the stator vanes of the fan stator in a separate duct in the axial direction and is only mixed with the air of the secondary duct downstream of the fan stator. The separate duct is formed by a plurality of hollow structures extending in the longitudinal direction each between two adjacent stator vanes of the fan stator, with the hollow structures having a closed circumference in cross-section.
대표청구항
▼
1. A device for bleeding compressor air in a turbofan engine, comprising: a primary flow duct,a secondary flow duct,a low-pressure compressor positioned in the primary flow duct,a fan stator arranged in the secondary flow duct downstream of a fan in a flow direction, the fan stator including stator
1. A device for bleeding compressor air in a turbofan engine, comprising: a primary flow duct,a secondary flow duct,a low-pressure compressor positioned in the primary flow duct,a fan stator arranged in the secondary flow duct downstream of a fan in a flow direction, the fan stator including stator vanes positioned around a circumference of the fan stator,an arrangement by which compressor air to be discharged from the low-pressure compressor is introducible into the secondary flow duct,with the arrangement including an air guiding flow duct into which the compressor air is guided upstream of the fan stator relative to the flow direction in the secondary flow duct, and is there guided past the stator vanes in a separate flow duct in an axial direction and is only mixed with air of the secondary flow duct downstream of the fan stator,the separate flow duct being formed by a plurality of separate hollow structures extending in a longitudinal direction each between two adjacent stator vanes, with the hollow structures each having a closed circumference in cross-section to form an individual tube duct positioned adjacent both a hub of the fan stator and the two adjacent stator vanes, the individual tube duct having two side walls separate from and positioned between the two adjacent stator vanes, and a radially inner wall separate from and positioned radially outwardly from the hub, the two side walls and radially inner wall together forming a portion of the closed circumference, the individual tube duct being fastened to an adjacent engine component. 2. The device in accordance with claim 1, wherein the fan stator includes a hub with a hub surface that delimits the secondary flow duct radially inwards and the separate flow duct at least in some sections is provided adjoining or adjacent to the hub surface in the secondary flow duct. 3. The device in accordance with claim 2, wherein the separate flow duct includes a cover with a plurality of covering panels arranged at a radial distance to the hub surface, with the hub surface forming a radially inner limitation and the covering panels forming a radially outer limitation of the separate flow duct. 4. The device in accordance with claim 3, wherein the covering panels in the circumferential direction include an extension such that they extend each between two adjacent stator vanes of the fan stator, with the two adjacent stator vanes providing a subdivision of the separate flow duct into partial ducts in a circumferential direction. 5. The device in accordance with claim 3, wherein the covering panels each include a supporting web extending perpendicularly in a direction of the hub surface and braced against the hub surface. 6. The device in accordance with claim 1, wherein the separate flow duct forms a separated annular space within the secondary flow duct. 7. The device in accordance with claim 1, wherein the closed hollow structures are rectangular in cross-section. 8. The device in accordance with claim 1, wherein the separate flow duct extends in the axial direction over a length such that an axially rear end of the separate flow duct ends at a distance of at least 10% of a profile chord length of one of the stator vanes downstream of an axial trailing edge of the one of the stator vanes. 9. The device in accordance with claim 1, wherein the separate flow duct is prolonged at an axially rear end of the separate flow duct such that the compressor air is blown into the secondary flow duct at a small angle relative to the axial direction of flow inside the secondary flow duct. 10. The device in accordance with claim 9, wherein a radially inner limitation of the separate flow duct extends downstream of the fan stator in the axial direction further than a radially outer limitation of the separate flow duct, with a protruding portion of the radially inner limitation having a curvature in a direction of the secondary flow duct and at an end of the protruding portion running out tangentially to the axial direction of flow in the secondary flow duct. 11. The device in accordance with claim 1, wherein the fan stator is arranged on an exterior of an intermediate casing of the turbofan engine, and the intermediate casing absorbs structural loads. 12. The device in accordance with claim 1, wherein the fan stator supports structural loads. 13. The device in accordance with claim 1, and further comprising additional struts arranged in the secondary flow duct downstream of the fan stator in the flow direction for supporting, in combination with the fan stator, structural loads. 14. The device in accordance with claim 1, wherein the air guiding flow duct guides the compressor air in a radial direction upstream of the fan stator. 15. A turbofan engine with a device in accordance with claim 1. 16. The device in accordance with claim 1, wherein the separate flow duct extends in the axial direction over a length such that an axially rear end of the separate flow duct ends at a distance of at least 30% of a profile chord length of one of the stator vanes downstream of an axial trailing edge of the one of the stator vanes. 17. The device in accordance with claim 1, wherein the separate flow duct extends in the axial direction over a length such that an axially rear end of the separate flow duct ends at a distance of at least 60% of a profile chord length of one of the stator vanes downstream of an axial trailing edge of the one of the stator vanes. 18. The device in accordance with claim 1, wherein the separate hollow structures are fastened to separate casing or other components of the device.
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