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Research Papers

Flow Field and Hot Streak Migration Through a High Pressure Cooled Vanes With Representative Lean Burn Combustor Outflow

[+] Author and Article Information
Tommaso Bacci

DIEF,
Department of Industrial Engineering,
University of Florence,
Florence 50139, Italy
e-mail: tommaso.bacci@htc.de.unifi.it

Tommaso Lenzi

DIEF,
Department of Industrial Engineering,
University of Florence,
Florence 50139, Italy
e-mail: tommaso.lenzi@htc.de.unifi.it

Alessio Picchi

DIEF,
Department of Industrial Engineering,
University of Florence,
Florence 50139, Italy
e-mail: alessio.picchi@htc.de.unifi.it

Lorenzo Mazzei

DIEF,
Department of Industrial Engineering,
University of Florence,
Florence 50139, Italy
e-mail: lorenzo.mazzei@htc.de.unifi.it

Bruno Facchini

DIEF,
Department of Industrial Engineering,
University of Florence,
Florence 50139, Italy
e-mail: bruno.facchini@unifi.it

Manuscript received June 22, 2018; final manuscript received June 25, 2018; published online December 4, 2018. Editor: Jerzy T. Sawicki.

J. Eng. Gas Turbines Power 141(4), 041020 (Dec 04, 2018) (12 pages) Paper No: GTP-18-1275; doi: 10.1115/1.4040714 History: Received June 22, 2018; Revised June 25, 2018

Modern lean burn aero-engine combustors make use of relevant swirl degrees for flame stabilization. Moreover, important temperature distortions are generated, in tangential and radial directions, due to discrete fuel injection and liner cooling flows respectively. At the same time, more efficient devices are employed for liner cooling and a less intense mixing with the mainstream occurs. As a result, aggressive swirl fields, high turbulence intensities, and strong hot streaks are achieved at the turbine inlet. In order to understand combustor-turbine flow field interactions, it is mandatory to collect reliable experimental data at representative flow conditions. While the separated effects of temperature, swirl, and turbulence on the first turbine stage have been widely investigated, reduced experimental data is available when it comes to consider all these factors together.In this perspective, an annular three-sector combustor simulator with fully cooled high pressure vanes has been designed and installed at the THT Lab of University of Florence. The test rig is equipped with three axial swirlers, effusion cooled liners, and six film cooled high pressure vanes passages, for a vortex-to-vane count ratio of 1:2. The relative clocking position between swirlers and vanes has been chosen in order to have the leading edge of the central NGV aligned with the central swirler. In order to generate representative conditions, a heated mainstream passes though the axial swirlers of the combustor simulator, while the effusion cooled liners are fed by air at ambient temperature. The resulting flow field exiting from the combustor simulator and approaching the cooled vane can be considered representative of a modern Lean Burn aero engine combustor with swirl angles above ±50 deg, turbulence intensities up to about 28% and maximum-to-minimum temperature ratio of about 1.25. With the final aim of investigating the hot streaks evolution through the cooled high pressure vane, the mean aerothermal field (temperature, pressure, and velocity fields) has been evaluated by means of a five-hole probe equipped with a thermocouple and traversed upstream and downstream of the NGV cascade.

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Figures

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Fig. 1

Trisector rig layout: three-dimensional (3D) CAD model (a) and sectional view (b)

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Fig. 2

NGV airfoil CAD model and cooling scheme

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Fig. 3

Comparison of blade loading between periodic reference and rig configuration

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Fig. 4

Mach number profiles at plane 41 midspan: comparison between CFD and experimental results

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Fig. 5

Scheme of the experimental facility

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Fig. 6

Five-hole probe along planes 40 and 41

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Fig. 7

Flow angles maps measured on plane 40: swirl and pitch angles

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Fig. 8

Nondimensional temperature map measured on plane 40

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Fig. 9

Pressure losses and secondary flows on plane 41

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Fig. 10

Pressure losses and secondary flows on plane 41: focus on right passage

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Fig. 11

Pressure loss coefficient on plane 41: 1D profiles

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Fig. 12

Nondimensional temperature maps measured on plane 41

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Fig. 13

Temperature distortion parameter on plane 41: 1D profiles

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Fig. 14

Summary of temperature distortions

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Fig. 15

Maximum temperature difference within left and right passage

Tables

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