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Pressure sensitive paint (PSP) has proven to be a powerful technique
for measuring the film cooling effectiveness; however, it is limited
to only the film cooling effectiveness. This project involves the
development of an experimental technique which combines both PSP and
temperature sensitive paint (TSP) to simultaneously obtain detailed
film
cooling effectiveness and heat transfer coefficient distributions. |
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This project
focuses on the internal cooling process of blades and vanes for the
advanced gas turbines used in various applications of today’s
modernized society. The extreme inlet temperatures of gas turbines
used in: fixed-wing aircraft, rotorcraft, tanks, trains, naval
vessels and landbased generators, motivate research to understand the flow
physics associated with rotor blade cooling performance, with aims
of improving the current internal cooling designs. In this project,
heat transfer coefficients are experimentally determined in various
trailing edge cooling channels. Different studies of a Reynolds
number range varying from 20,000 to 80,000, open the doors to
profound understanding of the effects of channel geometry, entrance
conditions, rib turbulators and ejection cases with respect to
heat transfer coefficients. |
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Publication:
Wright, L.M., and Gohardani, A.S., 2008, “Effect of Coolant
Ejection in Rectangular and Trapezoidal Trailing Edge Cooling
Passages at High Reynolds Numbers,” ASME Paper No. GT2008-50414,
Submitted for Presentation at 2008 ASME Turbo Expo, Berlin,
Germany. |
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This is an experimental study of flow through a radial TOBI system.
Included in the study is determination of flow coefficients of
various TOBI holes, flow coefficients through various rotating shaft
holes, and the swirl of the fluid downstream of the rotating shaft
holes. A small-scale rig is available to consider the effect of
hole geometry, pressure ratio, and velocity ratio on the various
flow coefficients and flow swirl. |
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Through the Mechanical Engineering senior design sequence we are
designing and fabricating a rig capable of considering the effect of
rotation on internal turbine blade cooling. The rig will be capable
of studying the effect of
rotation under advanced engine conditions:
Re = 5,000 –
100,000 , Ro = 0 – 0.75 , Bo = 0 - 3. |
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Publication:
Wright, L.M., and Desai, B.A, 2008, “Effect of
Upstream Ramp Geometry on the Film Cooling Effectiveness from
Cylindrical Inclined Holes,” ASME Paper No. GT2008-50348,
Submitted for Presentation at 2008 ASME Turbo Expo, Berlin,
Germany. |
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