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Research Papers

On Turbulence Measurements and Analyses in a Two-Stage Two-Spool Turbine Rig

[+] Author and Article Information
Sabine Bauinger

Institute for Thermal Turbomachinery
and Machine Dynamics,
Graz University of Technology,
Graz 8010, Austria
e-mail: sabine.bauinger@tugraz.at

Stephan Behre

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

Davide Lengani

Dipartimento di Macchine,
Sistemi Energetici e Transporti,
Università di Genova,
Genoa 16126, Italy

Yavuz Guendogdu

MTU Aero Engines,
Munich 80995, Germany

Franz Heitmeir

Institute for Thermal Turbomachinery
and Machine Dynamics,
Graz University of Technology,
Graz 8010, Austria

Emil Goettlich

Institute for Thermal Turbomachinery and
Machine Dynamics,
Graz University of Technology,
Graz 8010, Austria

1Corresponding author.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received August 28, 2015; final manuscript received November 24, 2016; published online March 7, 2017. Assoc. Editor: Guillermo Paniagua.

J. Turbomach 139(7), 071008 (Mar 07, 2017) (11 pages) Paper No: TURBO-15-1191; doi: 10.1115/1.4035508 History: Received August 28, 2015; Revised November 24, 2016

Since the experiment in turbulence research is of very high importance for evaluating turbulence hypothesis, turbulence measurements were carried out in a two-stage two-spool transonic turbine test rig at the Institute for Thermal Turbomachinery and Machine Dynamics in Graz in which the two rotors are counter-rotating with two different rotational speeds. For the current measurement campaign, triple hot-wire probes, which represent a very new measurement technique in this test rig, were used and their results validated with a fast response aerodynamic pressure probe (FRAPP). Based on the data measured with this device, turbulence intensities may be determined using a method called Fourier filtering. If the classical ensemble averaging procedure with only one trigger is applied, the periodic fluctuations of the other rotor will artificially increase the stochastic fluctuations. Therefore, the two trigger signals of the two rotors require a special analysis method, which was established at Graz University of Technology. The results from this method will be compared to the classical triple decomposition, which uses only one trigger signal. With this analysis tool, it is not only possible to evaluate unsteady signals triggered by one of the two rotors, but also the unsteady interactions of the rotors can be determined and investigated.

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References

Figures

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Fig. 1

Cross section through transonic test turbine facility (TTTF)

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Fig. 2

Probe head of the used triple-sensor hot wire probe and scheme of probe head to show the wire orientation

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Fig. 3

FFT using the trigger signal of the HP rotor (left side, peak at (1) BPF of the HP rotor and the LP rotor (right side, peak at (1) and (2) BPF of the LP rotor)

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Fig. 4

Schematic demonstration of rotor synchronic averaging (RSA [20])

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Fig. 5

FFT using rotor synchronic averaging; peaks at BPF of LP and HP rotor and at their interaction frequencies

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Fig. 6

FFT before Fourier filtering (left side, peaks at BPF of LP and HP rotor and their at interaction frequencies) and FFT after Fourier filtering (right side, peaks at BPFs and interaction frequencies are removed)

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Fig. 7

Flow field downstream of LP rotor, Mach number for one time-step using LP trigger (upper figure) and time-averaged (lower figure) [27]

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Fig. 8

Contour plot of turbulence intensity using HP trigger (see Eq. (5)) measured with hot wire probes, main structures coming from the TMTF can be detected

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Fig. 9

Contour plot of turbulence intensity using LP trigger (see Eq. (5)) measured with hot wire probes, in addition to the structures originating from the upstream stage also LP blade wakes can be seen

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Fig. 10

Contour plot of turbulence intensity using RSA (new postprocessing method) measured with hot wire probes, dashed circles show areas with most significant changes in turbulence intensity

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Fig. 11

Difference in turbulence intensity between postprocessing with LP trigger and rotor synchronic averaging

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Fig. 12

Comparison between turbulence intensities measured with hot wire probe (top) and FRAPP (bottom); main flow structures are marked in both figures

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Fig. 13

cm′, cu′, and cr′ in plane F made dimensionless with the mean absolute velocity in this plane (one time-step)

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Fig. 14

Four different time-steps of turbulence intensity showing one LP blade passing period

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