A turbine exhaust case (TEC) of a turbofan aeroengine includes a mixer for mixing exhaust gases with a bypass air stream, the TEC comprising an annular hub and the mixer surrounding the hub, and a plurality of deswirling struts circumferentially spaced apart with respect to a central axis of the TEC
A turbine exhaust case (TEC) of a turbofan aeroengine includes a mixer for mixing exhaust gases with a bypass air stream, the TEC comprising an annular hub and the mixer surrounding the hub, and a plurality of deswirling struts circumferentially spaced apart with respect to a central axis of the TEC and located entirely within an axial length of the mixer. The mixer defines a trailing edge having one or more upstream-most locations thereof where the mixing of the exhausted gases and the bypass air stream begins to take place. The deswirling struts each extend radially across the annular exhaust gas duct and interconnect the mixer and the hub, defining a trailing edge positioned upstream of and axially spaced away from the one or more upstream-most locations of the trailing edge of the mixer.
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1. A turbine exhaust case (TEC) of a turbofan aeroengine including a mixer for mixing exhaust gases flowing along a radially-inner surface of the mixer with a bypass airstream flowing along a radially-outer surface of the mixer, the TEC comprising: a hub and said mixer surrounding the hub, the mixer
1. A turbine exhaust case (TEC) of a turbofan aeroengine including a mixer for mixing exhaust gases flowing along a radially-inner surface of the mixer with a bypass airstream flowing along a radially-outer surface of the mixer, the TEC comprising: a hub and said mixer surrounding the hub, the mixer and the hub being annular, the mixer having lobes defining crests and valleys, the lobes being configured in a circumferential array and being axially extending, the crests and valleys being circumferentially alternating, the crests and valleys diverging from one another beginning at an upstream end of an axial length of the lobes and extending divergently from one another toward and terminating at a trailing edge of the lobes, the trailing edge defining a downstream end of the axial length of the lobes, the trailing edge of the lobes having a lobe trailing edge root defined at an upstream-most location of at least one cutout formed in the trailing edge of the lobes where mixing of the exhaust gases and the bypass airstream begins, the TEC further comprising a plurality of circumferentially spaced deswirling struts radially extending between the mixer and the hub and located entirely within the axial length of the lobes, the deswirling struts configured to attenuate a residual swirl condition of the exhaust gases, the residual swirl condition being defined upstream of the mixer and generated by a turbine of the turbofan aeroengine, a trailing edge of an outer end of the respective deswirling struts intersecting the mixer upstream of said upstream-most location of the at least one cutout, wherein the crests and valleys extend divergently from one another from a start location, and wherein a leading edge of the deswirling struts is positioned downstream from the start location. 2. The TEC as defined in claim 1 wherein the at least one cutout defines a scalloped trailing edge profile having a curved trailing edge section extending between respective adjacent crests and valleys, said upstream-most location of the trailing edge of the lobes being defined in the respective curved trailing edge sections. 3. The TEC as defined in claim 1 wherein the at least one cutout defines a jagged trailing edge profile having a plurality of downstream projecting tabs, said upstream-most location of the trailing edge of the lobes being defined between adjacent tabs. 4. The TEC as defined in claim 1 wherein the trailing edge of the respective deswirling struts intersects the mixer at a joint point of the trailing edge of the respective deswirling struts and the mixer. 5. The TEC as defined in claim 1 wherein the trailing edge of each of the deswirling struts is circumferentially aligned with a bottom of one of the valleys. 6. The TEC as defined in claim 1 wherein each of the valleys of the mixer is connected with a corresponding one of the deswirling struts. 7. The TEC as defined in claim 1 wherein every second one of the valleys of the mixer is connected with a corresponding one of the deswirling struts. 8. The TEC as defined in claim 1 wherein the deswirling struts are each cambered in a direction of an incoming swirling flow of the exhaust gases. 9. A turbofan aeroengine comprising a turbine exhaust case (TEC) positioned downstream of a turbine section for directing a gas flow exhausted from the turbine section, the TEC including a hub surrounded by a mixer having a circumferentially wavy configuration to form a plurality of axially extending lobes of the mixer, the mixer and the hub being annular, the lobes defining alternating crests and valleys extending divergently to and terminating at a trailing edge of the mixer, the crests defining internal axial passages for directing said exhausted gas flow to pass therethrough along a radially-inner surface of the mixer, and the valleys defining external axial passages for directing a bypass airstream to pass therethrough along a radially-outer surface of the mixer, resulting in a mixing action of said exhausted gas flow and said bypass airstream, the mixing action beginning to take place at one or more upstream-most locations of one or more cutouts formed in the trailing edge of the mixer earlier than at remaining locations of the trailing edge of the mixer, a plurality of circumferentially spaced apart deswirling struts radially extending between the mixer and the hub, and located entirely within an axial length of the lobes, the deswirling struts configured to attenuate a residual swirl condition of the exhaust gases, the residual swirl condition being defined upstream of the mixer and generated by the turbine section of the turbofan aeroengine, a tip point of a trailing edge of the respective deswirling struts being positioned upstream of said one or more upstream-most locations of the one or more cutouts formed in the trailing edge of the mixer and axially distanced therefrom by a predetermined axial clearance therebetween, wherein the crests and valleys extend divergently from one another from a start location, and wherein a leading edge of the deswirling struts is positioned downstream from the start location. 10. The turbofan aeroengine as defined in claim 9 wherein the one or more cutouts define a scalloped trailing edge profile having a curved trailing edge section extending between respective adjacent crests and valleys, said one or more upstream-most locations of the trailing edge of the mixer being defined in the respective curved trailing edge sections. 11. The turbofan aeroengine as defined in claim 9 wherein the one or more cutouts define a jagged trailing edge profile having a plurality of downstream projecting tabs, said one or more upstream-most locations of the trailing edge of the mixer being defined between adjacent tabs. 12. The turbofan aeroengine as defined in claim 9 wherein the tip point of the trailing edge of the respective deswirling struts is a joint point of the trailing edge of the respective deswirling struts and the mixer. 13. The turbofan aeroengine as defined in claim 9 wherein the trailing edge of each of the deswirling struts is circumferentially aligned with a bottom of one of the valleys.
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이 특허에 인용된 특허 (14)
Maguire, Addison C., Bypass gas turbine aeroengines and exhaust mixers therefor.
Huzzard Cunningham, Mark, Gas turbine engine exhaust mixer including circumferentially spaced-apart radial rows of tabs extending downstream on the radial walls, crests and troughs.
Wynosky Thomas A. (Madison CT) Streib Richard A. (Palm Beach Gardens FL) Campbell Charles A. (Palm Beach Gardens FL), Lobe mixer for gas turbine engine.
Farquhar Bannister W. (Bellevue WA) Sokhey Jagdish S. (Renton WA), Primary-secondary ventilated flow mixer nozzle for high bypass turbo fan jet propulsion system.
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