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Thermofluidics and Turbomachinery

  • Stuart A. Jacobson
Chapter
Part of the MEMS Reference Shelf book series (MEMSRS)

Abstract

The MIT MicroEngine rotor disk is less than 10 mm in diameter, which is more than two orders of magnitude smaller than that of a conventional aircraft gas turbine rotor disk. This significant length scale reduction impacts the underlying physics associated with the aerothermal design of the engine. Fluid dynamic and heat transfer parameters such as Reynolds number and Biot number in the MicroEngine are quite small, lying outside the commonly understood design space associated with gas turbine engines. The reduction in scale has a primarily negative impact on engine performance, although some benefits do arise as well.

Keywords

Mass Flow Rate Pressure Ratio Biot Number Centrifugal Compressor Thrust Bearing 
These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.

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Copyright information

© Springer Science+Business Media, LLC 2009

Authors and Affiliations

  • Stuart A. Jacobson
    • 1
  1. 1.Department of Aeronautics and AstronauticsMassachusetts Institute of TechnologyCambridgeUSA

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