Turbomachine comprising a plurality of fixed radial blades mounted upstream of the fan
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F01B-025/00
F02C-009/22
F02K-003/06
F01D-017/16
출원번호
US-0626507
(2015-02-19)
등록번호
US-9885291
(2018-02-06)
우선권정보
FR-12 57742 (2012-08-09)
발명자
/ 주소
Lecordix, Jean-Loic Herve
Bordoni, Nils
출원인 / 주소
SNECMA
대리인 / 주소
Oblon, McClelland, Maier & Neustadt, L.L.P.
인용정보
피인용 횟수 :
0인용 특허 :
8
초록▼
A bypass turbine engine including: an inner casing, an inter-duct casing, and an outer casing so as to define a primary duct between the inter-duct casing and the inner casing, and a secondary duct between the inter-duct casing and the outer casing; a rotary shaft including a movable fan including r
A bypass turbine engine including: an inner casing, an inter-duct casing, and an outer casing so as to define a primary duct between the inter-duct casing and the inner casing, and a secondary duct between the inter-duct casing and the outer casing; a rotary shaft including a movable fan including radial blades of which free ends face the outer casing of the turbine engine to compress an air flow in the secondary duct; a plurality of variable-pitch radial stator vanes mounted upstream of the movable fan so as to deflect the incident axial air prior to it being axially rectified by the movable fan in the secondary duct; and a system for individually regulating the pitch of the variable-pitch radial vanes if heterogeneity of the air flow in the secondary duct is detected, is provided.
대표청구항▼
1. A bypass turbine engine in which air flows circulate from upstream to downstream, the turbine engine extending axially and comprising: an inner casing, an inter-duct casing, and an outer casing so as to define a primary duct between the inter-duct casing and the inner casing, and a secondary duct
1. A bypass turbine engine in which air flows circulate from upstream to downstream, the turbine engine extending axially and comprising: an inner casing, an inter-duct casing, and an outer casing so as to define a primary duct between the inter-duct casing and the inner casing, and a secondary duct between the inter-duct casing and the outer casing;a rotary shaft comprising, at an upstream end of the rotary shaft, a movable fan comprising radial blades of which free ends face the outer casing of the turbine engine so as to compress an air flow at least in the secondary duct;a plurality of variable-pitch radial stator vanes mounted upstream of the movable fan, said variable-pitch radial stator vanes being configured to deflect incident axial air and the movable fan being configured to axially rectify said air deflected in the secondary duct; anda regulating system which individually regulates a pitch of the variable-pitch radial stator vanes if heterogeneity of the air flow in the secondary duct is detected,wherein the regulating system includes a first control ring, a second control ring, and a connecting rod assembly including a first connecting rod, a second connecting rod, a third connecting rod, and a fourth connecting rod, a first end of the first connecting rod being connecting to the first control ring, a first end of the second connecting rod being connected to the first connecting rod and a second end of the second connecting rod being connected to a first end of the third connecting rod, a second end of the third connecting rod being connected to a first end of the fourth connecting rod, a second end of the fourth connecting rod being connected to one of the variable-pitch radial stator vanes, and the third connecting rod being connected to the second control ring. 2. The turbine engine according to claim 1, wherein the inner casing, the inter-duct casing, and the outer casing are at a radial distance from one another in the turbine engine so as to define a turbine engine having a bypass ratio that is equal to 15. 3. The turbine engine according to claim 1, wherein a rotational speed of the free ends of the blades of the movable fan is less than 340 m/s. 4. The turbine engine according to claim 1, wherein the plurality of variable-pitch radial stator vanes extend in a same plane which is transverse to an axis of the turbine engine. 5. The turbine engine according to claim 1, wherein an axial distance between the plurality of variable-pitch radial stator vanes and the movable fan is between 0.1 and 10 times a mean chord of a variable-pitch radial stator vane. 6. The turbine engine according to claim 1, wherein the blades of the movable fan extend between the inner casing and the outer casing of the turbine engine. 7. The turbine engine according to claim 1, wherein each variable-pitch radial stator vane has an aerodynamic profile so as to accelerate flow of the incident air in accordance with a laminar flow. 8. The turbine engine according to claim 1, wherein each variable-pitch radial stator vane has a body which is movable in rotation about a radial axis. 9. The turbine engine according to claim 1, wherein each variable-pitch radial stator vane has a fixed body and a movable flap. 10. The turbine engine according to claim 1, wherein the plurality of variable-pitch radial stator vanes forms a planar transverse surface at a given pitch position of each of the variable-pitch radial stator vanes. 11. The turbine engine according to claim 1, wherein said first and second control rings are movably mounted in rotation about a longitudinal axis of the turbine engine on one of the inner casing or the outer casing. 12. The turbine engine according to claim 11, wherein the first connecting rod is movably mounted in rotation about a first substantially radial pivot pin and a second substantially radial pivot pin, the first pivot pin being mounted on said first control ring and the second pivot pin being configured to be positioned independently of the position of the first control ring, and the second connecting rod is pivotally mounted on the first connecting rod about a first hinge pin which is positioned at a first distance from said second pivot pin. 13. The turbine engine according to claim 12, wherein said first hinge pin is positioned between the first and second pivot pins. 14. The turbine engine according to claim 12, wherein the second pivot pin is mounted on the second control ring, and wherein the second connecting rod of said connecting rod assembly is pivotally mounted about the third pivot pin. 15. The turbine engine according to claim 12, wherein said the connecting rod assembly is arranged such that ratios between a variation of a pitch angle caused by a single movement of the first control ring and a variation of a pitch angle caused by a single movement of the second control ring are different for at least two of said variable-pitch radial stator vanes. 16. A method for adjusting the pitch of radial stator vanes in a turbine engine according to claim 12, during a maintenance or adjustment operation on the turbine engine, comprising: determining values for said first distance on the first connecting rod and for a second distance defined by a gap between the third pivot pin and a hinge pin of the fourth connecting rod, which fourth connecting rod is mounted on said third pivot pin, said values allowing a law for a given change in pitch angles to be obtained depending on a change in positions of the first and the second control ring; andadjusting at least one of the first distance and the second distance. 17. The turbine engine according to claim 12, wherein a pivot connection is arranged to connect said one of the variable-pitch radial stator vanes to said connecting rod assembly about a third, substantially radial pivot pin which is connected to the one of the variable-pitch radial stator vanes and offset along the longitudinal axis relative to a pitch pin of said one of the variable-pitch radial stator vanes. 18. The turbine engine according to claim 17, wherein the second pivot pin is mounted on the outer casing and the third connecting rod in said connecting rod assembly is movably mounted in rotation about a fourth, substantially radial pivot pin which is mounted on said second control ring. 19. The turbine engine according to claim 18, wherein the fourth pivot pin is positioned on the third connecting rod between a second hinge pin having the second connecting rod and a third hinge pin having the fourth connecting rod, said fourth connecting rod being pivotally mounted about the third pivot pin. 20. The turbine engine according to claim 18, wherein the fourth pivot pin is substantially in a same plane, which is perpendicular to the longitudinal axis, as a pitch pin of the one of the variable-pitch radial stator vanes. 21. The turbine engine according to claim 18, wherein the first and third connecting rods are substantially parallel to the longitudinal axis for at least one position of the first and second control rings. 22. A bypass turbine engine in which air flows circulate from upstream to downstream, the turbine engine extending axially and comprising: an inner casing, an inter-duct casing, and an outer casing so as to define a primary duct between the inter-duct casing and the inner casing, and a secondary duct between the inter-duct casing and the outer casing;a rotary shaft comprising, at an upstream end of the rotary shaft, a movable fan comprising radial blades of which free ends face the outer casing of the turbine engine so as to compress an air flow at least in the secondary ducta plurality of variable-pitch radial stator vanes mounted upstream of the movable fan, said variable-pitch radial stator vanes being configured to deflect incident axial air and the movable fan being configured to axially rectify said air deflected in the secondary duct; anda regulating system which individually regulates a pitch of the variable-pitch radial stator vanes if heterogeneity of the air flow in the secondary duct is detected,wherein each variable-pitch radial stator vanes extends radially between the inter-duct casing and the outer casing to which the variable-pitch radial stator vanes are fixed, andwherein the regulating system includes a first control ring, a second control ring, and at least two rods for connecting said first and second rings to each of said variable-pitch radial stator vanes.
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이 특허에 인용된 특허 (8)
Charbonnel Jean-Louis (Boissise Le Roi FRX), Control device for a stage of blades with variable pitch.
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