IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0178584
(2014-02-12)
|
등록번호 |
US-9709002
(2017-07-18)
|
우선권정보 |
FR-13 51379 (2013-02-18) |
발명자
/ 주소 |
- Pouyau, Guillaume
- Sirvin, Nicolas
|
출원인 / 주소 |
|
대리인 / 주소 |
Oblon, McClelland, Maier & Neustadt, L.L.P.
|
인용정보 |
피인용 횟수 :
0 인용 특허 :
8 |
초록
▼
A method of mixing in a discharge conduit, in a turbine engine with two or more flows, of a primary flow and a secondary flow, the two flows emerging in the discharge conduit by two coaxial ducts, separated by an internal housing which has an end downstream relative to the flow direction of the flow
A method of mixing in a discharge conduit, in a turbine engine with two or more flows, of a primary flow and a secondary flow, the two flows emerging in the discharge conduit by two coaxial ducts, separated by an internal housing which has an end downstream relative to the flow direction of the flows, the two coaxial ducts each being defined between an internal wall and an external wall, upstream of the downstream end of the internal housing, and the secondary flow surrounding the primary flow, is provided. The method includes disposing a divergent radial deflection device in the primary duct, spaced apart from the walls of the primary duct. A turbine engine including the deflection device is also provided.
대표청구항
▼
1. A method of mixing in a discharge conduit in a turbine engine with two flows being a primary flow and a secondary flow, the two flows emerging in said discharge conduit by two coaxial ducts, separated by an internal housing which has a downstream end, the two coaxial ducts being defined upstream
1. A method of mixing in a discharge conduit in a turbine engine with two flows being a primary flow and a secondary flow, the two flows emerging in said discharge conduit by two coaxial ducts, separated by an internal housing which has a downstream end, the two coaxial ducts being defined upstream of the downstream end of the internal housing by a primary duct in which the primary flow circulates and a secondary duct in which the secondary flow circulates, the secondary flow surrounding the primary flow, the method comprising: disposing a divergent radial deflection means in the primary duct, spaced apart from walls of said primary duct. 2. The method of mixing according to claim 1, wherein an alternation is organized azimuthally around an axis of the ducts between first zones where the primary flow is deflected and second zones where the primary flow is not deflected. 3. A turbine engine with two flows, comprising: a primary flow and a secondary flow, the two flows emerging in a discharge conduit by two coaxial ducts, separated by an internal housing which has a downstream end, the two coaxial ducts being defined upstream of the downstream end by a primary duct in which the primary flow circulates and a secondary duct in which the secondary flow circulates, the secondary flow surrounding the primary flow; anda device including a divergent radial deflection means disposed in the primary duct, spaced apart from walls of said primary duct, and a fixing means for positioning said deflection means in said primary duct. 4. The turbine engine according to claim 3, including a plurality of divergent radial deflection means distributed azimuthally around an axis of the primary duct. 5. The turbine engine according to claim 3, wherein the deflection means is constituted by an aileron of which a profile, in at least one axial plane of the primary duct passing through said aileron, is cambered in an opposite direction to an axis of the primary duct. 6. The turbine engine according to claim 3, having a radial temperature profile of the primary flow with a maximum spacing of the walls of the primary duct, wherein the deflection means is positioned in such a way that an upstream end thereof is located at a radius less than that of a maximum temperature. 7. The turbine engine according to claim 3, comprising structural arms in the primary duct holding the internal housing, the structural arms constituting the fixing means. 8. The turbine engine according to claim 7, wherein the deflection means is an aileron which extends symmetrically on either side of the structural arm. 9. The turbine engine according to claim 8, wherein a cross-section of the primary duct is circular and the deflection means are distributed angularly around an axis of the flow in a periodic manner, an azimuthal angular extension of each deflection means being equal to a half-period. 10. The turbine engine according to claim 4, including a means for extracting air in the secondary flow and a conduit for the extracted air emerging on a trailing edge of the radial deflection means. 11. The turbine engine according to claim 10, wherein the means for extracting air is formed by a scoop which is placed in the secondary flow and passes through the internal housing. 12. The turbine engine according to claim 10, comprising, in the primary duct, structural arms holding the internal housing, and wherein said conduit is formed by a pipeline passing through one of the structural arms. 13. The turbine engine according to claim 3, wherein at least one of the fixing means connects said deflection means to a first wall and to a second wall delimiting the primary duct, said first wall being constituted by a part of a wall of a central body of the turbine engine and said second wall being constituted by a wall of the internal housing. 14. The turbine engine according to claim 13, wherein a ferrule holds the ailerons which each constitute the deflection means, the ferrule being maintained by rods connected to said first wall and second wall of the primary duct.
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