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TECHNICAL PAPERS

Interaction of Shroud Leakage Flow and Main Flow in a Three-Stage LP Turbine

[+] Author and Article Information
Jochen Gier, Bertram Stubert, Bernard Brouillet, Laurent de Vito

 MTU Aero Engines, Dachauer Str. 665, Muenchen 80995, Germany

J. Turbomach 127(4), 649-658 (Mar 01, 2003) (10 pages) doi:10.1115/1.2006667 History: Received December 01, 2002; Revised March 01, 2003

Endwall losses significantly contribute to the overall losses in modern turbomachinery, especially when aerodynamic airfoil load and pressure ratios are increased. In turbines with shrouded airfoils a large portion of these losses are generated by the leakage flow across the shroud clearance. Generally the related losses can be grouped into losses of the leakage flow itself and losses caused by the interaction with the main flow in subsequent airfoil rows. In order to reduce the impact of the leakage flow and shroud design related losses a thorough understanding of the leakage losses and especially of the losses connected to enhancing secondary flows and other main flow interactions has to be understood. Therefore, a three stage LP turbine typical for jet engines is being investigated. For the three-stage test turbine 3D Navier-Stokes computations are performed simulating the turbine including the entire shroud cavity geometry in comparison with computations in the ideal flow path. Numerical results compare favorably against measurements carried out at the high altitude test facility at Stuttgart University. The differences of the simulations with and without shroud cavities are analyzed for several points of operation and a very detailed quantitative loss breakdown is presented.

Copyright © 2005 by American Society of Mechanical Engineers
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References

Figures

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Figure 1

View of test turbine with modeled cavities

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Figure 2

Mesh in third vane inner air seal (IAS2)

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Figure 3

Static pressure in second vane (V4) for cavity and ideal flow path computations

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Figure 4

Static pressure in third vane (V5) for cavity and ideal flow path computations

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Figure 5

Isentropic efficiency distribution and exit total pressure for cavity and ideal flow path in comparison to experimental data

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Figure 6

Stream traces on vale 4 (V4)

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Figure 7

Turbine efficiency Reynolds number lapse rate

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Figure 8

Flow structure and entropy in inner air seal IAS2 for two clearances, Re=300,000 (projection into meridional plane)

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Figure 9

Flow structure and entropy in outer air seal OAS2 for 1.2mm clearances, Re=300,000 (projection into meridional plane)

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Figure 10

Flow visualization on the hub of the second vane, Re=300K

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Figure 11

Leakage flow fraction, relative gap, relative gap area, and static pressure ratio for all airfoil seals

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Figure 12

Leakage flow in OAS for different Reynolds numbers

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Figure 13

Comparison of radial distribution of yaw angle at vane 4 inlet for ideal flow path and cavity computation

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Figure 14

Total pressure distribution in axial plane downstream of vane 4 (V4)

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Figure 15

Axial and absolute circumferential velocity in OAS1 (blade 3) in (m/s)

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Figure 16

Axial and absolute circumferential velocity in IAS2 (vane 4) in (m/s)

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Figure 17

Cavity related losses for turbine

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