Research Papers

Numerical and Experimental Analysis of the Effect of Variable Blade Row Spacing in a Subsonic Axial Turbine

[+] Author and Article Information
M. Restemeier

e-mail: restemeier@ist.rwth-aachen.de

P. Jeschke

Institute of Jet Propulsion and Turbomachinery,
RWTH Aachen University,
Aachen 52062, Germany

J. Gier

MTU Aero Engines,
Dachauer Strasse 665,
80955 Munich, Germany

1Address all correspondence to this author.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received August 23, 2011; final manuscript received October 17, 2011; published online November 8, 2012. Editor: David Wisler.

J. Turbomach 135(2), 021031 (Nov 08, 2012) (9 pages) Paper No: TURBO-11-1191; doi: 10.1115/1.4006587 History: Received August 23, 2011; Revised October 17, 2011

Numerical and experimental investigations have been performed to determine the effect of a variation of the interblade row axial gap on turbine efficiency. The geometry used in this study is the 1.5-stage axial flow turbine rig of the Institute of Jet Propulsion and Turbomachinery at Rhejnisch Westfalische Technische Hochshule (RWTH) Aachen University. The influence of the blade row spacing on aerodynamics has been analyzed by conducting steady and unsteady Reynolds-averaged Navier-Stokes (RANS) simulations as well as measurements in the cold air turbine test rig of the Institute. Both potential and viscous flow interactions, including secondary flow, were investigated. The results show an aerodynamic improvement of efficiency and favorable spatial distribution of secondary kinetic energy by reduction of the axial gap.

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Fig. 1

Side view of turbine test rig

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Fig. 2

Measurement planes and blading

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Fig. 3

Probes used for the traverse plane investigations

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Fig. 4

Measurement grid in S3 plane

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Fig. 5

Computational domain for one passage per blade row at midspan

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Fig. 6

Radial distribution of measured inflow profile

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Fig. 7

CFD-predicted overall performance

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Fig. 8

Axial growth of losses over entire turbine

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Fig. 9

Streamlines on rotor blade colored by entropy

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Fig. 10

Second stator suction side without LE1 wake

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Fig. 11

Second stator suction side with LE1 wake

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Fig. 12

Radial distribution mass-averaged absolute streamwise vorticity in MP3

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Fig. 13

Measured turbine operating map

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Fig. 14

Comparison of CFD and experimental data

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Fig. 15

Time-averaged Mach number downstream the rotor

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Fig. 16

RMS turbulence downstream the second stator

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Fig. 17

Simulation results for the 2D calculation




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