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Research Papers

Blade Triggered Excitation of Periodically Unsteady Impinging Jets for Efficient Turbine Liner Segment Cooling

[+] Author and Article Information
Christian Scherhag

Institute of Gas Turbines
and Aerospace Propulsion,
Technische Universität Darmstadt,
Otto-Berndt-Str. 2,
Darmstadt 64287, Germany
e-mail: scherhag@glr.tu-darmstadt.de

Jan Paul Geiermann, Fabian Wartzek, Heinz-Peter Schiffer

Institute of Gas Turbines
and Aerospace Propulsion,
Technische Universität Darmstadt,
Otto-Berndt-Str. 2,
Darmstadt 64287, Germany

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received November 9, 2015; final manuscript received November 13, 2015; published online January 20, 2016. Editor: Kenneth C. Hall.

J. Turbomach 138(5), 051005 (Jan 20, 2016) (10 pages) Paper No: TURBO-15-1254; doi: 10.1115/1.4032145 History: Received November 09, 2015; Revised November 13, 2015

In the present study, an application for efficient cooling of turbine liner segments employing pulsating impinging jets was investigated. A combined numerical and experimental study was conducted to evaluate the design of a case cavity device which utilizes the periodically unsteady pressure distribution caused by the rotor blades to excite a pulsating impinging jet. Through an opening between the main annulus and a case cavity, pressure pulses from the rotor blades propagated into this cavity and caused a strong pressure oscillation inside. The unsteady computational fluid dynamics (CFD) results were in good qualitative agreement with the measurement data obtained using high-frequency pressure transducers and hot wire anemometry. Furthermore, the numerical study revealed the formation of distinct toroidal vortex structures at the nozzle outlet as a result of the jet pulsation. Within the scope of the measurements, the influence of the operating point on the pressure propagation inside the cavity was investigated. The dependence of shape and amplitude of the pressure oscillation on engine speed and stage pressure ratio was found to be in accordance with an analytical consideration.

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Figures

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Fig. 1

Darmstadt Transonic Compressor

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Fig. 2

Compressor stage and investigated case cavity device

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Fig. 3

Dimensions of the cavity device and schematic illustration of cooling air flow and pressure oscillation

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Fig. 4

Instrumentation applied to the inner cavity

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Fig. 5

Close-up view of the computational domain

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Fig. 6

Ratio of grid spacing to Kolmogorov length scale in an axial slice through the cavity device

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Fig. 7

Pressure distribution in the cavity device

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Fig. 8

Frequency spectrum of the pressure signal monitored in the transient CFD computation close to the opening between main annulus and inner cavity

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Fig. 9

Velocity variation over time at the nozzle outlet

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Fig. 10

Visualization of vortex structures using isosurfaces of q = 9 × 109 s−2 colored by vorticity

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Fig. 11

Frequency spectrum encompassing the recorded pressure signals of all 19 pressure transducers

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Fig. 12

Schematic illustration of the data averaging procedure

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Fig. 13

Unsteady pressure distribution: experimental results above, CFD results below

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Fig. 14

Comparison of experimental and numerical results for the velocity fluctuation at the nozzle outlet

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Fig. 15

Analytical solution for the shift of the central pressure maximum following Eq. (14)

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Fig. 16

Influence of engine speed and pressure ratio on the shift of the central pressure maximum

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Fig. 17

Relation between pressure amplitude and velocity fluctuation for different pressure ratios

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