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Research Papers

Redesign of a Low Speed Turbine Stage Using a New Viscous Inverse Design Method

[+] Author and Article Information
Benedikt Roidl

Department of Mechanical and Industrial Engineering, Concordia University, 1455 de Maisonneuve, West, Montreal, QC H3G 1M8, Canadab_roidl@encs.concordia.ca

Wahid Ghaly1

Department of Mechanical and Industrial Engineering, Concordia University, 1455 de Maisonneuve, West, Montreal, QC H3G 1M8, Canadaghaly@encs.concordia.ca

1

Corresponding author.

J. Turbomach 133(1), 011009 (Sep 09, 2010) (9 pages) doi:10.1115/1.4000491 History: Received August 28, 2008; Revised February 10, 2009; Published September 09, 2010; Online September 09, 2010

The midspan section of a low speed subsonic turbine stage that is built and tested at DFVLR, Cologne, is redesigned using a new inverse blade design method, where the blade walls move with a virtual velocity distribution derived from the difference between the current and target pressure distributions on the blade surfaces. This new inverse method is fully consistent with the viscous flow assumption and is implemented into the time-accurate solution of the Reynolds-averaged Navier–Stokes equations. An algebraic Baldwin–Lomax turbulence model is used for turbulence closure. The mixing plane approach is used to couple the stator and rotor regions. The computational fluid dynamics (CFD) analysis formulation is first assessed against the turbine stage experimental data. The inverse formulation that is implemented in the same CFD code is assessed for its robustness and merits. The inverse design method is then used to study the effect of the rotor pressure loading on the blade shape and stage performance. It is also used to simultaneously redesign both stator and rotor blades for improved stage performance. The results show that by carefully tailoring the target pressure loading on both blade rows, improvement can be achieved in the stage performance.

Copyright © 2011 by American Society of Mechanical Engineers
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References

Figures

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Figure 1

2D cascade geometry and notation

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Figure 2

Wall virtual velocity and displacement

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Figure 3

Inverse design iterative process

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Figure 4

E/TU-3 stage: mach isolines

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Figure 5

Mesh close-up near rotor LE and TE

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Figure 6

Initial, target, and design stator geometry

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Figure 7

Initial, target, and design stator pressure distributions

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Figure 8

Rotor redesign: original and target pressure loadings

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Figure 9

Case 1: rotor geometry

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Figure 10

Case 1: rotor isentropic Mach number and pressure loading

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Figure 11

Case 2: rotor isentropic Mach number and pressure loading

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Figure 12

Case 2: rotor geometry

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Figure 19

E/TU-3 stage redesign II: stator isentropic Mach number and pressure loading

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Figure 18

E/TU-3 stage redesign II: stator and rotor geometry

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Figure 17

E/TU-3 stage redesign I: stator and rotor geometry

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Figure 16

E/TU-3 stage redesign I: rotor isentropic Mach number and pressure loading

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Figure 15

E/TU-3 stage redesign I: stator isentropic Mach number and pressure loading

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Figure 14

Case 3: rotor isentropic Mach number and pressure loading

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Figure 13

Case 3: rotor geometry

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Figure 20

E/TU-3 stage redesign II: rotor isentropic Mach number and pressure loading

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