초록 ▼

A method and apparatus for reducing avian collisions with wind turbines 70, wherein a design or pattern 90 is placed on the rotor blades 60 of a wind turbine 70 for reducing the motion smear of the image of the rotor blades 60 on the bird's retina 30. When the motion smear on the bird's retina 30 is

A method and apparatus for reducing avian collisions with wind turbines 70, wherein a design or pattern 90 is placed on the rotor blades 60 of a wind turbine 70 for reducing the motion smear of the image of the rotor blades 60 on the bird's retina 30. When the motion smear on the bird's retina 30 is reduced, the bird 10 is capable of detecting the presence of the rotor blades 60 more easily, thus allowing the bird 10 to re-direct its flight path and avoid colliding with the wind turbine 70. The design principle is that a pattern placed in a given location on one rotor blade 60 is not repeated in the same location on any other rotor blades 60 on the wind turbine 70.

대표청구항 ▼

A method and apparatus for reducing avian collisions with wind turbines 70, wherein a design or pattern 90 is placed on the rotor blades 60 of a wind turbine 70 for reducing the motion smear of the image of the rotor blades 60 on the bird's retina 30. When the motion smear on the bird's retina 30 is

A method and apparatus for reducing avian collisions with wind turbines 70, wherein a design or pattern 90 is placed on the rotor blades 60 of a wind turbine 70 for reducing the motion smear of the image of the rotor blades 60 on the bird's retina 30. When the motion smear on the bird's retina 30 is reduced, the bird 10 is capable of detecting the presence of the rotor blades 60 more easily, thus allowing the bird 10 to re-direct its flight path and avoid colliding with the wind turbine 70. The design principle is that a pattern placed in a given location on one rotor blade 60 is not repeated in the same location on any other rotor blades 60 on the wind turbine 70. l disposed within the compressor, and an aperture providing communication between compressor wheel and the annular channel, the inner deflector ring comprising: a first substantially radially extending surface, for obstructing flow along the annular channel, and a second substantially axially extending surface. 14. An inner deflector ring as defined in claim 13 further comprising: a third axially extending surface extending along the annular channel and separated from the first axially extending surface by the second radially extending surface, which is disposed therebetween. 15. A turbocharger system having a noise reduction device comprising: a bypass port compressor having a housing, a concentric inner radial wall and outer radial wall collectively defining the compressor inlet, the inner radial wall circumscribing a central channel, and an annular channel interposed between the outer radial wall and the inner radial wall, the annular channel being disposed concentrically around the central channel, a compressor outlet, a compressor wheel having a plurality of vanes, the wheel located between the inlet and outlet and in communication with both the central and annular channels; and an inner deflector disposed within the annular channel, having a first surface extending radially across the annular channel, and a second surface extending axially along the annular channel, to partially obstruct flow into and out of the annular channel. 16. A turbocharger system as defined in claim 15 further comprising: a noise suppressor disposed within the compressor inlet, wherein the noise suppressor is coupled to an inner surface of the outer radial wall. 17. A turbocharger system as defined in claim 16 wherein: the noise suppressor is cylindrical. 18. A turbocharger system as defined in claim 17 wherein: the outer diameter of the noise suppressor is greater than the outer diameter of the annular channel. 19. A turbocharger system as defined in claim 17 wherein: the inner diameter of the noise suppressor is less than the inner diameter of the annular channel. 20. A turbocharger system as defined in claim 15 wherein: the noise suppressor is substantially "C" shaped in cross-section. 21. A turbocharger system as defined in claim 15 wherein: the noise suppressor is substantially "J" shaped in cross-section. 22. A turbocharger system as defined in claim 15 wherein: the noise suppressor is substantially "L" shaped in cross-section. ing condition thereby to inhibit the cam from returning to the unlocking condition.