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Research Papers

Development and Application of a Fast-Response Total Temperature Probe for Turbomachinery

[+] Author and Article Information
Martin C. Arenz

Institute of Aircraft Propulsion Systems,
University of Stuttgart,
Pfaffenwaldring 6,
Stuttgart 70569, Germany
e-mail: martin.arenz@ila.uni-stuttgart.de

Björn Weigel, Jan Habermann, Stephan Staudacher

Institute of Aircraft Propulsion Systems,
University of Stuttgart,
Pfaffenwaldring 6,
Stuttgart 70569, Germany

Martin G. Rose

Department of Engineering and Design,
University of Sussex,
Sussex House, Falmer,
Brighton BN1 9RH, UK

Wolfgang Berns

Berns Engineers GmbH,
Friedrichshafener Straße 3,
Gilching 82205, Germany

Ewald Lutum

MTU Aero Engines AG,
Dachauer Straße 665,
München 80995, Germany

1Corresponding author.

2Present address: ZF Friedrichshafen AG, Löwentaler Straße 20, Friedrichshafen 88046, Germany.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received October 23, 2016; final manuscript received November 3, 2016; published online January 24, 2017. Editor: Kenneth Hall.

J. Turbomach 139(5), 051010 (Jan 24, 2017) (9 pages) Paper No: TURBO-16-1280; doi: 10.1115/1.4035278 History: Received October 23, 2016; Revised November 03, 2016

The measurement of unsteady total temperature is of great interest for the examination of loss mechanisms in turbomachinery with respect to the improvement of the efficiency. Since conventional thermocouples are limited in frequency response, several fast-response total temperature probes have been developed over the past years. To improve the spatial resolution compared to these existing probes and maintaining a high temporal resolution, a new fast-response total temperature probe has been developed at the Institute of Aircraft Propulsion Systems (ILA), Stuttgart, Germany in cooperation with Berns Engineers, Gilching, Germany. The design of the probe allows a sensitive measuring surface below 1 mm2. A detailed insight into the design of the probe, the measurement principle, the calibration process, and an estimation of the measurement uncertainty is given in the present paper. Furthermore, to prove the functionality of the probe, first experimental results of a simple test bed and of area traverses downstream of the first rotor of a two-stage low pressure turbine are presented. It is shown, that the new probe is capable of detecting rotor characteristic effects as well as rotor-stator-interactions. In addition, a hot-spot is investigated downstream of the first rotor of the turbine, and the findings are compared to the effects known from the literature.

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References

Figures

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Fig. 1

Schematic diagram of the total temperature probe; top-view (left), section (right)

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Fig. 2

Comparison of the results of the impulse response technique with the Cook–Felderman-algorithm and an analytical solution for a periodic boundary condition

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Fig. 3

Schematic diagram of calibration test bed

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Fig. 4

Comparison of the original and transformed wall temperature with linear fit

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Fig. 5

Results of the thermal product calibration for three probes

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Fig. 6

Comparison of the frequency response of the total temperature probe to a fast-response pressure probe

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Fig. 7

Meridional view of ATRD-turbine with hot-spot nozzle

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Fig. 8

SST-diagram of unsteady total temperature at MP8 at rotor 1 exit for the isothermal case

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Fig. 9

Comparison of the normalized total temperature of the fast-response total temperature probe (left) and the thermocouple of the five-hole probe (right) at rotor exit (MP8)

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Fig. 10

A 360 deg traverse of the total temperature at turbine inlet (MP4)

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Fig. 11

SST-diagram of unsteady total temperature at MP8 at rotor 1 exit for the hot-spot case

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Fig. 12

Space-time-diagram of unsteady total temperature at z/l = 65%

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