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Research Papers

Investigation of Nonaxisymmetric Endwall Contouring and Three-Dimensional Airfoil Design in a 1.5 Stage Axial Turbine—Part II: Experimental Validation

[+] Author and Article Information
Jens Niewoehner

Institute of Jet Propulsion and Turbomachinery,
RWTH Aachen University,
Templergraben 55,
Aachen 52062, Germany
e-mail: jens.niewoehner@man.eu

Thorsten Poehler, Peter Jeschke

Institute of Jet Propulsion and Turbomachinery,
RWTH Aachen University,
Templergraben 55,
Aachen 52062, Germany

Yavuz Guendogdu

MTU Aero Engines AG,
Dachauer Strasse 665,
Munich 80995, Germany

1Present address: MAN Diesel & Turbo SE, Steinbrinkstr. 1, Oberhausen 46145, Germany.

2Corresponding author.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received November 23, 2014; final manuscript received December 17, 2014; published online February 3, 2015. Editor: Kenneth C. Hall.

J. Turbomach 137(8), 081010 (Aug 01, 2015) (12 pages) Paper No: TURBO-14-1302; doi: 10.1115/1.4029477 History: Received November 23, 2014; Revised December 17, 2014; Online February 03, 2015

This paper is the second part of a two-part paper reporting on the increase in efficiency of a 1.5 stage axial test rig turbine with the use of nonaxisymmetric endwalls and 3D airfoil design. Contoured endwalls were developed for the inlet guide vane separately, as well as in combination with a bowed radial profile stacking. In addition, a contour endwall was applied to the hub of the unshrouded rotor. In Part I, the design of the profiled endwalls and 3D airfoils is presented, as well as a detailed analysis of the steady and unsteady computational fluid dynamics (CFD) results. Part II reports on the experimental validation of the numerical results. A distinct increase in mechanical efficiency for both new configurations in good agreement with the numerical results is observed. Additionally, performance map measurements demonstrate that the new designs are also beneficial under off-design conditions. Five- and three-hole-probes as well as fast-response total pressure probes are used to investigate the new designs. The main effect is the homogenization of the yaw angle behind the first stator.

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Figures

Grahic Jump Location
Fig. 4

Probe rake downstream of the second stator

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Fig. 3

Cross-sectional view of the turbine

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Fig. 2

Total pressure at the inlet of the turbine

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Fig. 1

Cold-air turbine test rig

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Fig. 10

Axial development of entropy of the new configurations in comparison to the basic design (unsteady CFD)

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Fig. 5

Measurement grid for probe traversing

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Fig. 6

Five-hole-probe (left), three-hole probe (middle), and fast-response total pressure probe (right)

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Fig. 12

Streamwise vorticity at the exit of the first stator for the three stator designs (unsteady CFD)

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Fig. 7

Selected configurations for the experimental investigations (shroud of the first stator is blanked)

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Fig. 8

Performance map for the three designs investigated at 100%, 90%, and 80% speed

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Fig. 9

Evaluation of the efficiency for the new configurations at constant stage loading

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Fig. 11

Yaw angle at the exit of the first stator (measurement plane 1): unsteady CFD (top), five-hole-probe (mid), and three-hole-probe (bottom)

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Fig. 13

Streamwise vorticity at the exit of the first stator (measurement plane 1) for the three stator designs (five-hole-probe)

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Fig. 15

Time-averaged streamwise vorticity at the exit of the rotor for the three configurations (unsteady CFD)

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Fig. 16

RMS of the random part of total pressure at the exit of the rotor (measurement plane 2, fast-response total pressure probe): basic design (top), ewc–ewc (mid), and f3d–ewc (bottom)

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Fig. 14

Total pressure loss coefficient ω at the exit of the first stator: unsteady CFD (top) and five-hole-probe (bottom, measurement plane 1)

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