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Please use this identifier to cite or link to this item: https://dspace.lboro.ac.uk/2134/32973

Title: Impact of flow unsteadiness on steady-state gas-path stagnation temperature measurements
Authors: Bonham, Clare
Brend, Mark
Spencer, Adrian
Tanimizu, Katsuyoshi
Wise, Dylan
Keywords: Temperature measurement
Flow (Dynamics)
Steady state
Mach number
Unsteady flow
Heat losses
Issue Date: 2018
Publisher: © ASME (American Society of Mechanical Engineers)
Citation: BONHAM, C. ... et al, 2018. Impact of flow unsteadiness on steady-state gas-path stagnation temperature measurements. Journal of Engineering for Gas Turbines and Power, 140 (12), paper no. 122602.
Abstract: Steady-state stagnation temperature probes are used during gas turbine engine testing as a means of characterising turbomachinery component performance. The probes are located in the high-velocity gas-path, where temperature recovery and heat transfer effects cause a shortfall between the measured temperature and the flow stagnation temperature. To improve accuracy, the measurement shortfall is corrected post-test using data acquired at representative Mach numbers in a steady aerodynamic calibration facility. However, probes installed in engines are typically subject to unsteady flows, which are characterised by periodic variations in Mach number and temperature caused by the wakes shed from upstream blades. The present work examines the impact of this periodic unsteadiness on stagnation temperature measurements by translating probes between jets with dissimilar Mach numbers. For conventional Kiel probes in unsteady flows, a greater temperature measurement shortfall is recorded compared to equivalent steady flows, which is related to greater conductive heat loss from the temperature sensor. This result is important for the application of post-test corrections, since an incorrect value will be applied using steady calibration data. A new probe design with low susceptibility to conductive heat losses is therefore developed, which is shown to deliver the same performance in both steady and unsteady flows. Measurements from this device can successfully be corrected using steady aerodynamic calibration data, resulting in improved stagnation temperature accuracy compared to conventional probe designs. This is essential for resolving in-engine component performance to better than +/-0.5% across all component pressure ratios.
Description: This paper is closed access until 6th August 2019.
Sponsor: This research was funded by the European Commission under the Framework 7 STARGATE project.
Version: Accepted for publication
DOI: 10.1115/1.4040285
URI: https://dspace.lboro.ac.uk/2134/32973
Publisher Link: https://doi.org/10.1115/1.4040285
ISSN: 0742-4795
Appears in Collections:Closed Access (Aeronautical and Automotive Engineering)

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