Research Papers: Gas Turbines: Combustion, Fuels, and Emissions

Validation of Surface Temperature Measurements on a Combustor Liner Under Full-Load Conditions Using a Novel Thermal History Paint

[+] Author and Article Information
Robert Krewinkel, Jens Färber, Ulrich Orth, Dirk Frank, Martin Lauer

MAN Diesel & Turbo SE,
Steinbrinkstraße 1,
Oberhausen D-46145, Germany

Christopher Pilgrim, Alvaro Yañez Gonzalez, Jörg Feist, Raffaele Saggese, Stéphane Berthier

Sensor Coating Systems Ltd.,
Level 1&2 Bessemer Building,
Imperial College Road,
London SW7 2AZ, UK

Silvia Araguas-Rodriguez

Sensor Coating Systems Ltd.,
Level 1&2 Bessemer Building,
Imperial College Road,
London SW7 2AZ, UK;
Imperial College London,
London SW7 2AZ, UK

Contributed by the Combustion and Fuels Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received August 1, 2016; final manuscript received September 1, 2016; published online November 2, 2016. Editor: David Wisler.

J. Eng. Gas Turbines Power 139(4), 041508 (Nov 02, 2016) (8 pages) Paper No: GTP-16-1384; doi: 10.1115/1.4034724 History: Received August 01, 2016; Revised September 01, 2016

The ever-increasing requirements on gas turbine efficiency and the simultaneous demand for reduced emissions, necessitate much more accurate calculations of the combustion process and combustor wall temperatures. Thermal history paints (THPs) is an innovative alternative to the established measurement techniques, but so far only a limited number of tests have been conducted under real engine conditions. A typical THP comprises oxide ceramic pigments and a water-based binder. The ceramic is synthesized to be amorphous and when heated it crystallizes, permanently changing the microstructure. The ceramic is doped with lanthanide ions to make it phosphorescent and as the structure of the material changes, so do the phosphorescent properties of the material. By measuring the phosphorescence, the maximum temperature of exposure can be determined, enabling postoperation measurements at ambient conditions. This paper describes a test in which THP was applied to an impingement-cooled front panel from a combustor of an industrial gas turbine. The panel was instrumented with a thermocouple (TC), and thermal paint was applied to the cold side of the impingement plate. The THP was applied to the hot-gas side of this plate for validation against the other measurement techniques and to evaluate its resilience against the reacting hot gas environment. The durability and temperature results of the three different measurement techniques are discussed. It is shown that the THP exhibited greater durability compared to the conventional thermal paint. Furthermore, the new technology provided detailed measurements indicating local temperature variations and global variations over the complete component.

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Fig. 1

Impingement cooling (based on Ref. [2])

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Fig. 2

A single measured luminescence decay time

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Fig. 3

MAN's advanced can combustor [21]

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Fig. 4

High-pressure test rig at the DLR in Cologne

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Fig. 5

The data from the thermocouple attached to the front panel of the combustor with the range of the thermal paint indicated as a vertical bar

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Fig. 6

An overview of the instrumentation coupled with the linear slides used to acquire the measurements on the THP on the front panel of the combustor

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Fig. 7

Part of the generic calibration dataset on stainless steel and nickel alloy substrates. The error bars represent the standard deviation on five repeat measurements at the same location multiplied by two to increase visibility.

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Fig. 8

Thermal paint (impingement) side of the front panel of the test combustor after testing

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Fig. 9

Close up images of Fig. 8 (left): the location of the thermocouple (box (a)) and the spallation of the thermal paint (box (b)) after testing

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Fig. 10

THP (hot gas) side of the front panel of the test combustor after testing

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Fig. 11

The measurement locations of the THP shown in three dimensions (distortion exaggerated)

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Fig. 12

The normalized temperature measurement data from the THP shown as a contour plot

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Fig. 13

The normalized temperature data from the fifth evaluation radius. The cool spots observed in Fig. 12 (labeled A) are indicated on the plot.

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Fig. 14

The contours plot from the THP (color) overlaid on the photograph of the thermal paint (grayscale) where the normalized temperature values associated with the isothermals are labeled

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Fig. 15

Data cross section from the red dashed line in Fig. 14 providing a comparison of the temperature measurements from the THP and thermal paint




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