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RESEARCH PAPERS

Influence of Aerodynamic Loading on Rotor-Stator Aerodynamic Interaction in a Two-Stage Low Pressure Research Turbine

[+] Author and Article Information
Edward Canepa

 DIMSET—Università di Genova, I-16145 Genova, Italyedward.canepa@unige.it

Piergiorgio Formosa

 DIMSET—Università di Genova, I-16145 Genova, Italypiergiorgio.formosa@unige.it

Davide Lengani

 DIMSET—Università di Genova, I-16145 Genova, Italydavide.lengani@unige.it

Daniele Simoni

 DIMSET—Università di Genova, I-16145 Genova, Italydaniele.simoni@unige.it

Marina Ubaldi

 DIMSET—Università di Genova, I-16145 Genova, Italyzunmp@unige.it

Pietro Zunino

 DIMSET—Università di Genova, I-16145 Genova, Italypietro.zunino@unige.it

J. Turbomach 129(4), 765-772 (Aug 04, 2006) (8 pages) doi:10.1115/1.2720498 History: Received July 24, 2006; Revised August 04, 2006

The unsteady flow within a two-stage low-pressure research turbine equipped with high lift profiles has been investigated in detail for three different aerodynamic loading conditions. Experiments have been carried out at low speed. Velocity and turbulence intensity in the blade-to-blade plane at midspan have been measured by means of a crossed hot-wire probe, upstream and downstream of each blade row. The probe has been traversed circumferentially over 1.5 bladings pitch and the phase-locked data acquisition and ensemble average technique have been used to reconstruct the flow in space and time. The effects of multistage configuration have been identified and analyzed by considering the velocity components and turbulence intensity. Potential interaction from the downstream blading in relative motion, periodic wake perturbations from the upstream blading and preceding stage perturbations make the flow in the second stage extremely complex. Overall the flow downstream of rotors is perturbed in space by upstream and downstream stators, while flow downstream of stators is mostly perturbed in time by rotor effects. As expected, high lift profiles are significantly sensitive to incidence variation, with this effect further enhanced by the multistage cumulative interactions.

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Copyright © 2007 by American Society of Mechanical Engineers
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Figures

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Figure 1

Meridional section of the turbine model

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Figure 2

Two-stage low-pressure turbine bladings

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Figure 3

Measuring point locations

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Figure 4

Intermediate loading conditions flowfield

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Figure 5

Time evolution of the absolute flow angle for y∕g=0.75 at section 2

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Figure 6

Comparison of flowfields at section 3 for high and low loading

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Figure 7

Time averaged flow angle circumferential distribution in section 3

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Figure 8

Comparison of flowfields at section 4 for high and low loading

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Figure 9

Time averaged absolute velocity and turbulence intensity circumferential distribution in section 4

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Figure 10

Comparison of flowfields at section 5 for high and low loading

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Figure 11

Time averaged relative flow angle circumferential distributions in sections 3 and 5, at two different loading conditions

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