Title page for ETD etd-06112009-063614
|Type of Document
||Janakiraman, S. V.
||Fluid flow and heat transfer in transonic turbine cascades
||Master of Science
|Moses, Hal L.
|Date of Defense
The aerodynamic and thermodynamic performance of an aircraft gas turbine directly affects
the fuel consumption of the engine and the life of the turbine components. Hence, it is
important to be able to understand and predict the fluid flow and heat transfer in turbine
blades to enable the modifications and improvements in the design process. The use of numerical
experiments for the above purposes is becoming increasingly common. The present
thesis is involved with the development of a flow solver for turbine flow and heat transfer
A 3-D Navier-Stokes code, the Moore Elliptic Flow Program (MEFP) is used to calculate
steady flow and heat transfer in turbine rotor cascades. Successful calculations were performed
on two different rotor profiles using a one-equation q-L transitional turbulence model.
A series of programs was developed for the post-processing of the output from the flow solver.
The calculations revealed details of the flow including boundary layer development, trailing
edge shocks, flow transition and stagnation and peak heat transfer rates.
The calculated pressure distributions, losses, transition ranges, boundary layer parameters
and peak heat transfer rates to the blade are compared with the available experimental
data. The comparisons indicate that the q-L transitional turbulence model is successful in
predicting flows in transonic turbine blade rows. The results also indicate that the calculated
loss levels are independent of the gridding used while the heat transfer rate predictions improve
with finer grids.
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