The Experts below are selected from a list of 177 Experts worldwide ranked by ideXlab platform

Rolf Sondergaard - One of the best experts on this subject based on the ideXlab platform.

  • Toward the Expansion of Low-Pressure-Turbine Airfoil Design Space
    Journal of Turbomachinery, 2013
    Co-Authors: T. J. Praisner, E. A. Grover, D. C. Knezevici, I. Popovic, S. A. Sjolander, J. P. Clark, Rolf Sondergaard
    Abstract:

    Future Engine requirements, including high-altitude flight of unmanned air vehicles as well as an impetus to reduce Engine Cost and weight, are challenging the current state of the art in low-pressure-turbine airfoil design. These new requirements present low-Reynolds number challenges as well as the need for high-performance, high-lift design concepts. Here, we report on an effort to expand the relatively well established aerodynamic design space for low-pressure turbine airfoils through the application of recent developments in transition modeling to airfoil design. Analytical and experimental midspan performance data and predicted loadings are presented for four high-lift airfoil designs based on the Pack B velocity triangles. The new designs represent a systematic expansion of low-pressure turbine airfoil design space through the application of high-lift design concepts for front- and aft-loaded airfoils. All four designs performed as predicted across a range of operationally representative Reynolds numbers. Full-span loss data for the new high-lift designs reveal increased endwall losses, which, with the application of nonaxisymmetric endwall contouring, have been substantially reduced. Taken holistically, the results presented here demonstrate that accurate transition modeling provides a reliable method to develop optimized, very high-lift airfoil designs. However, further improvements in endwall-loss mitigation technologies are required to enable the implementation of the very high-lift technology presented here in Engine systems.

  • Toward the Expansion of Low-Pressure-Turbine Airfoil Design Space (Postprint)
    2008
    Co-Authors: T. J. Praisner, Rolf Sondergaard, E. A. Grover, D. C. Knezevici, I. Popovic, S. A. Sjolander, J. P. Clark, P. J. Koch
    Abstract:

    Abstract : Future Engine requirements, including high-altitude flight of unmanned air vehicles as well as a movement to reduce Engine Cost and weight, are challenging the current state of the art in low-pressure-turbine airfoil design. These new requirements present low-Reynolds number challenges as well as the need for high-performance high-lift design concepts. Here we report on an effort to expand the relatively well established design space for low-pressure turbine airfoils. Analytical and experimental mid-span performance data and loadings are presented for four new airfoil designs based on the Pack B velocity triangles. The new designs represent a systematic expansion of low-pressure turbine airfoil design space through the application of high-lift design concepts for front- and aft-loaded airfoils. Taken holistically, the results presented here demonstrate accurate transition modeling provides a reliable method to develop optimized, very high-lift airfoil designs.

  • toward the expansion of low pressure turbine airfoil design space
    ASME Turbo Expo 2008: Power for Land Sea and Air, 2008
    Co-Authors: T. J. Praisner, E. A. Grover, D. C. Knezevici, I. Popovic, S. A. Sjolander, J. P. Clark, Rolf Sondergaard
    Abstract:

    Future Engine requirements, including high-altitude flight of unmanned air vehicles, as well as an impetus to reduce Engine Cost and weight, are challenging the current state of the art in low-pressure-turbine airfoil design. These new requirements present low-Reynolds number challenges as well as the need for high-performance, high-lift design concepts. Here we report on an effort to expand the relatively well established aerodynamic design space for low-pressure turbine airfoils through the application of recent developments in transition modeling to airfoil design. Analytical and experimental mid-span performance data and predicted loadings are presented for four high-lift airfoil designs based on the Pack B velocity triangles. The new designs represent a systematic expansion of low-pressure turbine airfoil design space through the application of high-lift design concepts for front- and aft-loaded airfoils. All four designs performed as predicted across a range of operationally representative Reynolds numbers. Full-span loss data for the new high-lift designs reveal increased endwall losses, which, with the application of non-axisymmetric endwall contouring, have been substantially reduced. Taken holistically, the results presented here demonstrate that accurate transition modeling provides a reliable method to develop optimized, very high-lift airfoil designs. However, further improvements in endwall-loss mitigation technologies are required to enable the implementation of the very high-lift technology presented here in Engine systems.© 2008 ASME

T. J. Praisner - One of the best experts on this subject based on the ideXlab platform.

  • Toward the Expansion of Low-Pressure-Turbine Airfoil Design Space
    Journal of Turbomachinery, 2013
    Co-Authors: T. J. Praisner, E. A. Grover, D. C. Knezevici, I. Popovic, S. A. Sjolander, J. P. Clark, Rolf Sondergaard
    Abstract:

    Future Engine requirements, including high-altitude flight of unmanned air vehicles as well as an impetus to reduce Engine Cost and weight, are challenging the current state of the art in low-pressure-turbine airfoil design. These new requirements present low-Reynolds number challenges as well as the need for high-performance, high-lift design concepts. Here, we report on an effort to expand the relatively well established aerodynamic design space for low-pressure turbine airfoils through the application of recent developments in transition modeling to airfoil design. Analytical and experimental midspan performance data and predicted loadings are presented for four high-lift airfoil designs based on the Pack B velocity triangles. The new designs represent a systematic expansion of low-pressure turbine airfoil design space through the application of high-lift design concepts for front- and aft-loaded airfoils. All four designs performed as predicted across a range of operationally representative Reynolds numbers. Full-span loss data for the new high-lift designs reveal increased endwall losses, which, with the application of nonaxisymmetric endwall contouring, have been substantially reduced. Taken holistically, the results presented here demonstrate that accurate transition modeling provides a reliable method to develop optimized, very high-lift airfoil designs. However, further improvements in endwall-loss mitigation technologies are required to enable the implementation of the very high-lift technology presented here in Engine systems.

  • Toward the Expansion of Low-Pressure-Turbine Airfoil Design Space (Postprint)
    2008
    Co-Authors: T. J. Praisner, Rolf Sondergaard, E. A. Grover, D. C. Knezevici, I. Popovic, S. A. Sjolander, J. P. Clark, P. J. Koch
    Abstract:

    Abstract : Future Engine requirements, including high-altitude flight of unmanned air vehicles as well as a movement to reduce Engine Cost and weight, are challenging the current state of the art in low-pressure-turbine airfoil design. These new requirements present low-Reynolds number challenges as well as the need for high-performance high-lift design concepts. Here we report on an effort to expand the relatively well established design space for low-pressure turbine airfoils. Analytical and experimental mid-span performance data and loadings are presented for four new airfoil designs based on the Pack B velocity triangles. The new designs represent a systematic expansion of low-pressure turbine airfoil design space through the application of high-lift design concepts for front- and aft-loaded airfoils. Taken holistically, the results presented here demonstrate accurate transition modeling provides a reliable method to develop optimized, very high-lift airfoil designs.

  • toward the expansion of low pressure turbine airfoil design space
    ASME Turbo Expo 2008: Power for Land Sea and Air, 2008
    Co-Authors: T. J. Praisner, E. A. Grover, D. C. Knezevici, I. Popovic, S. A. Sjolander, J. P. Clark, Rolf Sondergaard
    Abstract:

    Future Engine requirements, including high-altitude flight of unmanned air vehicles, as well as an impetus to reduce Engine Cost and weight, are challenging the current state of the art in low-pressure-turbine airfoil design. These new requirements present low-Reynolds number challenges as well as the need for high-performance, high-lift design concepts. Here we report on an effort to expand the relatively well established aerodynamic design space for low-pressure turbine airfoils through the application of recent developments in transition modeling to airfoil design. Analytical and experimental mid-span performance data and predicted loadings are presented for four high-lift airfoil designs based on the Pack B velocity triangles. The new designs represent a systematic expansion of low-pressure turbine airfoil design space through the application of high-lift design concepts for front- and aft-loaded airfoils. All four designs performed as predicted across a range of operationally representative Reynolds numbers. Full-span loss data for the new high-lift designs reveal increased endwall losses, which, with the application of non-axisymmetric endwall contouring, have been substantially reduced. Taken holistically, the results presented here demonstrate that accurate transition modeling provides a reliable method to develop optimized, very high-lift airfoil designs. However, further improvements in endwall-loss mitigation technologies are required to enable the implementation of the very high-lift technology presented here in Engine systems.© 2008 ASME

I. Popovic - One of the best experts on this subject based on the ideXlab platform.

  • Toward the Expansion of Low-Pressure-Turbine Airfoil Design Space
    Journal of Turbomachinery, 2013
    Co-Authors: T. J. Praisner, E. A. Grover, D. C. Knezevici, I. Popovic, S. A. Sjolander, J. P. Clark, Rolf Sondergaard
    Abstract:

    Future Engine requirements, including high-altitude flight of unmanned air vehicles as well as an impetus to reduce Engine Cost and weight, are challenging the current state of the art in low-pressure-turbine airfoil design. These new requirements present low-Reynolds number challenges as well as the need for high-performance, high-lift design concepts. Here, we report on an effort to expand the relatively well established aerodynamic design space for low-pressure turbine airfoils through the application of recent developments in transition modeling to airfoil design. Analytical and experimental midspan performance data and predicted loadings are presented for four high-lift airfoil designs based on the Pack B velocity triangles. The new designs represent a systematic expansion of low-pressure turbine airfoil design space through the application of high-lift design concepts for front- and aft-loaded airfoils. All four designs performed as predicted across a range of operationally representative Reynolds numbers. Full-span loss data for the new high-lift designs reveal increased endwall losses, which, with the application of nonaxisymmetric endwall contouring, have been substantially reduced. Taken holistically, the results presented here demonstrate that accurate transition modeling provides a reliable method to develop optimized, very high-lift airfoil designs. However, further improvements in endwall-loss mitigation technologies are required to enable the implementation of the very high-lift technology presented here in Engine systems.

  • Toward the Expansion of Low-Pressure-Turbine Airfoil Design Space (Postprint)
    2008
    Co-Authors: T. J. Praisner, Rolf Sondergaard, E. A. Grover, D. C. Knezevici, I. Popovic, S. A. Sjolander, J. P. Clark, P. J. Koch
    Abstract:

    Abstract : Future Engine requirements, including high-altitude flight of unmanned air vehicles as well as a movement to reduce Engine Cost and weight, are challenging the current state of the art in low-pressure-turbine airfoil design. These new requirements present low-Reynolds number challenges as well as the need for high-performance high-lift design concepts. Here we report on an effort to expand the relatively well established design space for low-pressure turbine airfoils. Analytical and experimental mid-span performance data and loadings are presented for four new airfoil designs based on the Pack B velocity triangles. The new designs represent a systematic expansion of low-pressure turbine airfoil design space through the application of high-lift design concepts for front- and aft-loaded airfoils. Taken holistically, the results presented here demonstrate accurate transition modeling provides a reliable method to develop optimized, very high-lift airfoil designs.

  • toward the expansion of low pressure turbine airfoil design space
    ASME Turbo Expo 2008: Power for Land Sea and Air, 2008
    Co-Authors: T. J. Praisner, E. A. Grover, D. C. Knezevici, I. Popovic, S. A. Sjolander, J. P. Clark, Rolf Sondergaard
    Abstract:

    Future Engine requirements, including high-altitude flight of unmanned air vehicles, as well as an impetus to reduce Engine Cost and weight, are challenging the current state of the art in low-pressure-turbine airfoil design. These new requirements present low-Reynolds number challenges as well as the need for high-performance, high-lift design concepts. Here we report on an effort to expand the relatively well established aerodynamic design space for low-pressure turbine airfoils through the application of recent developments in transition modeling to airfoil design. Analytical and experimental mid-span performance data and predicted loadings are presented for four high-lift airfoil designs based on the Pack B velocity triangles. The new designs represent a systematic expansion of low-pressure turbine airfoil design space through the application of high-lift design concepts for front- and aft-loaded airfoils. All four designs performed as predicted across a range of operationally representative Reynolds numbers. Full-span loss data for the new high-lift designs reveal increased endwall losses, which, with the application of non-axisymmetric endwall contouring, have been substantially reduced. Taken holistically, the results presented here demonstrate that accurate transition modeling provides a reliable method to develop optimized, very high-lift airfoil designs. However, further improvements in endwall-loss mitigation technologies are required to enable the implementation of the very high-lift technology presented here in Engine systems.© 2008 ASME

J. P. Clark - One of the best experts on this subject based on the ideXlab platform.

  • Toward the Expansion of Low-Pressure-Turbine Airfoil Design Space
    Journal of Turbomachinery, 2013
    Co-Authors: T. J. Praisner, E. A. Grover, D. C. Knezevici, I. Popovic, S. A. Sjolander, J. P. Clark, Rolf Sondergaard
    Abstract:

    Future Engine requirements, including high-altitude flight of unmanned air vehicles as well as an impetus to reduce Engine Cost and weight, are challenging the current state of the art in low-pressure-turbine airfoil design. These new requirements present low-Reynolds number challenges as well as the need for high-performance, high-lift design concepts. Here, we report on an effort to expand the relatively well established aerodynamic design space for low-pressure turbine airfoils through the application of recent developments in transition modeling to airfoil design. Analytical and experimental midspan performance data and predicted loadings are presented for four high-lift airfoil designs based on the Pack B velocity triangles. The new designs represent a systematic expansion of low-pressure turbine airfoil design space through the application of high-lift design concepts for front- and aft-loaded airfoils. All four designs performed as predicted across a range of operationally representative Reynolds numbers. Full-span loss data for the new high-lift designs reveal increased endwall losses, which, with the application of nonaxisymmetric endwall contouring, have been substantially reduced. Taken holistically, the results presented here demonstrate that accurate transition modeling provides a reliable method to develop optimized, very high-lift airfoil designs. However, further improvements in endwall-loss mitigation technologies are required to enable the implementation of the very high-lift technology presented here in Engine systems.

  • Toward the Expansion of Low-Pressure-Turbine Airfoil Design Space (Postprint)
    2008
    Co-Authors: T. J. Praisner, Rolf Sondergaard, E. A. Grover, D. C. Knezevici, I. Popovic, S. A. Sjolander, J. P. Clark, P. J. Koch
    Abstract:

    Abstract : Future Engine requirements, including high-altitude flight of unmanned air vehicles as well as a movement to reduce Engine Cost and weight, are challenging the current state of the art in low-pressure-turbine airfoil design. These new requirements present low-Reynolds number challenges as well as the need for high-performance high-lift design concepts. Here we report on an effort to expand the relatively well established design space for low-pressure turbine airfoils. Analytical and experimental mid-span performance data and loadings are presented for four new airfoil designs based on the Pack B velocity triangles. The new designs represent a systematic expansion of low-pressure turbine airfoil design space through the application of high-lift design concepts for front- and aft-loaded airfoils. Taken holistically, the results presented here demonstrate accurate transition modeling provides a reliable method to develop optimized, very high-lift airfoil designs.

  • toward the expansion of low pressure turbine airfoil design space
    ASME Turbo Expo 2008: Power for Land Sea and Air, 2008
    Co-Authors: T. J. Praisner, E. A. Grover, D. C. Knezevici, I. Popovic, S. A. Sjolander, J. P. Clark, Rolf Sondergaard
    Abstract:

    Future Engine requirements, including high-altitude flight of unmanned air vehicles, as well as an impetus to reduce Engine Cost and weight, are challenging the current state of the art in low-pressure-turbine airfoil design. These new requirements present low-Reynolds number challenges as well as the need for high-performance, high-lift design concepts. Here we report on an effort to expand the relatively well established aerodynamic design space for low-pressure turbine airfoils through the application of recent developments in transition modeling to airfoil design. Analytical and experimental mid-span performance data and predicted loadings are presented for four high-lift airfoil designs based on the Pack B velocity triangles. The new designs represent a systematic expansion of low-pressure turbine airfoil design space through the application of high-lift design concepts for front- and aft-loaded airfoils. All four designs performed as predicted across a range of operationally representative Reynolds numbers. Full-span loss data for the new high-lift designs reveal increased endwall losses, which, with the application of non-axisymmetric endwall contouring, have been substantially reduced. Taken holistically, the results presented here demonstrate that accurate transition modeling provides a reliable method to develop optimized, very high-lift airfoil designs. However, further improvements in endwall-loss mitigation technologies are required to enable the implementation of the very high-lift technology presented here in Engine systems.© 2008 ASME

S. A. Sjolander - One of the best experts on this subject based on the ideXlab platform.

  • Toward the Expansion of Low-Pressure-Turbine Airfoil Design Space
    Journal of Turbomachinery, 2013
    Co-Authors: T. J. Praisner, E. A. Grover, D. C. Knezevici, I. Popovic, S. A. Sjolander, J. P. Clark, Rolf Sondergaard
    Abstract:

    Future Engine requirements, including high-altitude flight of unmanned air vehicles as well as an impetus to reduce Engine Cost and weight, are challenging the current state of the art in low-pressure-turbine airfoil design. These new requirements present low-Reynolds number challenges as well as the need for high-performance, high-lift design concepts. Here, we report on an effort to expand the relatively well established aerodynamic design space for low-pressure turbine airfoils through the application of recent developments in transition modeling to airfoil design. Analytical and experimental midspan performance data and predicted loadings are presented for four high-lift airfoil designs based on the Pack B velocity triangles. The new designs represent a systematic expansion of low-pressure turbine airfoil design space through the application of high-lift design concepts for front- and aft-loaded airfoils. All four designs performed as predicted across a range of operationally representative Reynolds numbers. Full-span loss data for the new high-lift designs reveal increased endwall losses, which, with the application of nonaxisymmetric endwall contouring, have been substantially reduced. Taken holistically, the results presented here demonstrate that accurate transition modeling provides a reliable method to develop optimized, very high-lift airfoil designs. However, further improvements in endwall-loss mitigation technologies are required to enable the implementation of the very high-lift technology presented here in Engine systems.

  • Toward the Expansion of Low-Pressure-Turbine Airfoil Design Space (Postprint)
    2008
    Co-Authors: T. J. Praisner, Rolf Sondergaard, E. A. Grover, D. C. Knezevici, I. Popovic, S. A. Sjolander, J. P. Clark, P. J. Koch
    Abstract:

    Abstract : Future Engine requirements, including high-altitude flight of unmanned air vehicles as well as a movement to reduce Engine Cost and weight, are challenging the current state of the art in low-pressure-turbine airfoil design. These new requirements present low-Reynolds number challenges as well as the need for high-performance high-lift design concepts. Here we report on an effort to expand the relatively well established design space for low-pressure turbine airfoils. Analytical and experimental mid-span performance data and loadings are presented for four new airfoil designs based on the Pack B velocity triangles. The new designs represent a systematic expansion of low-pressure turbine airfoil design space through the application of high-lift design concepts for front- and aft-loaded airfoils. Taken holistically, the results presented here demonstrate accurate transition modeling provides a reliable method to develop optimized, very high-lift airfoil designs.

  • toward the expansion of low pressure turbine airfoil design space
    ASME Turbo Expo 2008: Power for Land Sea and Air, 2008
    Co-Authors: T. J. Praisner, E. A. Grover, D. C. Knezevici, I. Popovic, S. A. Sjolander, J. P. Clark, Rolf Sondergaard
    Abstract:

    Future Engine requirements, including high-altitude flight of unmanned air vehicles, as well as an impetus to reduce Engine Cost and weight, are challenging the current state of the art in low-pressure-turbine airfoil design. These new requirements present low-Reynolds number challenges as well as the need for high-performance, high-lift design concepts. Here we report on an effort to expand the relatively well established aerodynamic design space for low-pressure turbine airfoils through the application of recent developments in transition modeling to airfoil design. Analytical and experimental mid-span performance data and predicted loadings are presented for four high-lift airfoil designs based on the Pack B velocity triangles. The new designs represent a systematic expansion of low-pressure turbine airfoil design space through the application of high-lift design concepts for front- and aft-loaded airfoils. All four designs performed as predicted across a range of operationally representative Reynolds numbers. Full-span loss data for the new high-lift designs reveal increased endwall losses, which, with the application of non-axisymmetric endwall contouring, have been substantially reduced. Taken holistically, the results presented here demonstrate that accurate transition modeling provides a reliable method to develop optimized, very high-lift airfoil designs. However, further improvements in endwall-loss mitigation technologies are required to enable the implementation of the very high-lift technology presented here in Engine systems.© 2008 ASME