Abstract: A method of assembling an ejector is provided, wherein the method includes providing a motive nozzle tip having a centerline axis and including a nozzle tip edge having at least one protrusion extending through a plane substantially normal to the centerline axis. The method also includes coupling the motive nozzle tip to the ejector.

Abstract: A blade for a wind turbine includes a total backward twist of between approximately 6 degrees and approximately 15 degrees between an outer approximately 1 percent to approximately 10 percent of a rotor radius of the blade; and a total normalized chord change of between approximately one percent and approximately two percent between the outer approximately 1 percent to approximately 10 percent of the rotor radius of the blade.

Abstract: A blade for a wind turbine includes a total backward twist of between approximately 6 degrees and approximately 15 degrees between an outer approximately 1 percent to approximately 10 percent of a rotor radius of the blade.

Abstract: A method of assembling an ejector is provided, wherein the method includes providing a motive nozzle tip having a centerline axis and including a nozzle tip edge having at least one protrusion extending through a plane substantially normal to the centerline axis. The method also includes coupling the motive nozzle tip to the ejector.

Abstract: A method of assembling an ejector is provided, wherein the method includes providing a motive nozzle tip having a centerline axis and including a nozzle tip edge having at least one protrusion extending through a plane substantially normal to the centerline axis. The method also includes coupling the motive nozzle tip to the ejector.

Abstract: Embodiments of the present invention may provide real-time monitoring of a compressor section to determine the possibility of a crack forming on a rotating blade. The present invention does not require the shutdown of the machine. The present invention may be configured to automatically raise an alarm if the acoustic signature of the compressor changes in way that may be consistent with the cracking of a blade.

Abstract: A blade for a wind turbine includes a total backward twist of between approximately 6 degrees and approximately 15 degrees between an outer approximately 1 percent to 10 percent of a rotor radius of the blade; and an approximate planform distribution within the following ranges r/R c/R(LE) c/R(TE) .96 0.60 to 0.65% ?1.42 to ?1.34% .968 0.54 to 0.59% ?1.31 to ?1.34% .974 0.39 to 0.58% ?1.36 to ?1.22% .9806 0.13 to 0.57% ?1.45 to ?1.06% .9856 ?0.23 to 0.56%?? ?1.56 to ?0.74% .9906 ?0.76 to 0.55%?? ?1.74 to ?0.24% .9956 ?1.44 to 0.54%?? ?1.99 to 0.23%?? 1.00 ?2.17 to 0.54%?? ?2.27 to 0.44%?? where “r/R” is an approximate normalized distance outward from a center of rotation of the blade along a span of the blade; and “c/R(LE)” and “c/R(TE)” are approximate relative positions of a leading (LE) and trailing edge (TE) of a chord “c” expressed as a percentage of a distance outward from the center of rotation at each r/R.

Abstract: Disposed at or toward the trailing edge of one or more nozzles associated with a jet engine are injection ports which can selectively be made to discharge a water stream into a nozzle flow stream for the purpose of increasing turbulence in somewhat of a similar fashion as mechanically disposed chevrons have done in the known art. Unlike mechanically disposed chevrons of the known art, the fluid flow may be secured thereby increasing the engine efficiency. Various flow patterns, water pressures, orifice designs or other factors can be made operative to provide desired performance characteristics.

Abstract: Embodiments of the present invention may provide real-time monitoring of a compressor section to determine the possibility of a crack forming on a rotating blade. The present invention does not require the shutdown of the machine. The present invention may be configured to automatically raise an alarm if the acoustic signature of the compressor changes in way that may be consistent with the cracking of a blade.

Abstract: A blade for a wind turbine includes a chord of length “c” positioned with a leading edge tip chord angle and trailing edge tip chord angle of between approximately 45 and 75 degrees; a tip having a shear web plane radii distribution in the ranges of L/c (%) R/c (%) ?0-10% 1.03-3.68% 30-40% 2.91-5.79% 60-70% 1.77-2.5%? ?90-100% 0.229-.350%? where “L/c” is a range of an approximate normalized location along the chord line expressed as a percentage of the chord length from a leading edge of the blade; and where “R/c” is a range of an approximate normalized shear web plane tip radius expressed as a percentage of the chord length, for each normalized location L/c.

Abstract: A wind turbine blade includes a permeable flap extending from a trailing edge of the blade.

Abstract: A blade for a wind turbine includes a chord of length “c” positioned with a leading edge tip chord angle and trailing edge tip chord angle of between approximately 45 and 75 degrees; a tip having a shear web plane radii distribution in the ranges of L/c (%) R/c (%) ?0-10% 1.03-3.68% 30-40% 2.91-5.79% 60-70% 1.77-2.5%? ?90-100% 0.229-.350%? where “L/c” is a range of an approximate normalized location along the chord line expressed as a percentage of the chord length from a leading edge of the blade; and where “R/c” is a range of an approximate nornalized shear web plane tip radius expressed as a percentage of the chord length, for each normalized location L/c.

Abstract: A blade for a wind turbine includes a total backward twist of between approximately 6 degrees and approximately 15 degrees between an outer approximately 1 percent to approximately 10 percent of a rotor radius of the blade; and a total normalized chord change of between approximately one percent and approximately two percent between the outer approximately 1 percent to approximately 10 percent of the rotor radius of the blade.

Abstract: A blade for a wind turbine includes a total backward twist of between approximately 6 degrees and approximately 15 degrees between an outer approximately 1 percent to approximately 10 percent of a rotor radius of the blade.

Abstract: A blade for a wind turbine includes a total backward twist of between approximately 6 degrees and approximately 15 degrees between an outer approximately 1 percent to 10 percent of a rotor radius of the blade; and an approximate planform distribution within the following ranges r/R c/R(LE) c/R(TE) .96 0.60 to 0.65% ?1.42 to ?1.34% .968 0.54 to 0.59% ?1.31 to ?1.34% .974 0.39 to 0.58% ?1.36 to ?1.22% .9806 0.13 to 0.57% ?1.45 to ?1.06% .9856 ?0.23 to 0.56%?? ?1.56 to ?0.74% .9906 ?0.76 to 0.55%?? ?1.74 to ?0.24% .9956 ?1.44 to 0.54%?? ?1.99 to 0.23%?? 1.00 ?2.17 to 0.54%?? ?2.27 to 0.44%?? where “r/R” is an approximate normalized distance outward from a center of rotation of the blade along a span of the blade; and “c/R(LE)” and “c/R(TE)” are approximate relative positions of a leading (LE) and trailing edge (TE) of a chord “c” expressed as a percentage of a distance outward from the center of rotation at each r/R.

Abstract: A wind turbine blade, includes a sensor, arranged upstream from a trailing edge of the blade for measuring an airflow characteristic near a surface of the blade; and an actuator, arranged downstream from the sensor, for adjusting the airflow in response to the measured characteristic.

Abstract: Disposed at or toward the trailing edge of one or more nozzles associated with a jet engine are injection ports which can selectively be made to discharge a water stream into a nozzle flow stream for the purpose of increasing turbulence in somewhat of a similar fashion as mechanically disposed chevrons have done in the known art. Unlike mechanically disposed chevrons of the known art, the fluid flow may be secured thereby increasing the engine efficiency. Various flow patterns, water pressures, orifice designs or other factors can be made operative to provide desired performance characteristics.

Abstract: Methods and apparatus for suppressing cell howl with negligible impact on engine test conditions are described. The apparatus, in an exemplary embodiment includes a flow distorter configured to be positioned close to a nozzle exit of an engine nozzle, and a flow distorter support for maintaining the flow distorter at a selected location. The flow distorter is adjustably secured to the support so that a distance at which a tip of the distorter is located relative to support is adjustable.