Development of New Single and High-Density Heat Flux Gauges for Unsteady Heat Transfer Measurements in a Rotating Transonic Turbine
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| Language: | English |
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The Ohio State University / OhioLINK
2021
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| Online Access: | http://rave.ohiolink.edu/etdc/view?acc_num=osu1608551902273547 |
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ndltd-OhioLink-oai-etd.ohiolink.edu-osu1608551902273547 |
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English |
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Aerospace Engineering Mechanical Engineering Engineering Experiments Heat Flux Gauges Double-Sided Heat Flux Gauges Thin-film Instrumentation Short Duration Facility Heat Transfer Turbomachinery High Pressure Turbine Rotating Experimental |
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Aerospace Engineering Mechanical Engineering Engineering Experiments Heat Flux Gauges Double-Sided Heat Flux Gauges Thin-film Instrumentation Short Duration Facility Heat Transfer Turbomachinery High Pressure Turbine Rotating Experimental Celestina, Richard A. Development of New Single and High-Density Heat Flux Gauges for Unsteady Heat Transfer Measurements in a Rotating Transonic Turbine |
| author |
Celestina, Richard A. |
| author_facet |
Celestina, Richard A. |
| author_sort |
Celestina, Richard A. |
| title |
Development of New Single and High-Density Heat Flux Gauges for Unsteady Heat Transfer Measurements in a Rotating Transonic Turbine |
| title_short |
Development of New Single and High-Density Heat Flux Gauges for Unsteady Heat Transfer Measurements in a Rotating Transonic Turbine |
| title_full |
Development of New Single and High-Density Heat Flux Gauges for Unsteady Heat Transfer Measurements in a Rotating Transonic Turbine |
| title_fullStr |
Development of New Single and High-Density Heat Flux Gauges for Unsteady Heat Transfer Measurements in a Rotating Transonic Turbine |
| title_full_unstemmed |
Development of New Single and High-Density Heat Flux Gauges for Unsteady Heat Transfer Measurements in a Rotating Transonic Turbine |
| title_sort |
development of new single and high-density heat flux gauges for unsteady heat transfer measurements in a rotating transonic turbine |
| publisher |
The Ohio State University / OhioLINK |
| publishDate |
2021 |
| url |
http://rave.ohiolink.edu/etdc/view?acc_num=osu1608551902273547 |
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AT celestinaricharda developmentofnewsingleandhighdensityheatfluxgaugesforunsteadyheattransfermeasurementsinarotatingtransonicturbine |
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1719487751411204096 |
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ndltd-OhioLink-oai-etd.ohiolink.edu-osu16085519022735472021-10-07T05:10:41Z Development of New Single and High-Density Heat Flux Gauges for Unsteady Heat Transfer Measurements in a Rotating Transonic Turbine Celestina, Richard A. Aerospace Engineering Mechanical Engineering Engineering Experiments Heat Flux Gauges Double-Sided Heat Flux Gauges Thin-film Instrumentation Short Duration Facility Heat Transfer Turbomachinery High Pressure Turbine Rotating Experimental This document presents the development and implementation of a new generation of double-sided heat-flux gauges at The Ohio State University Gas Turbine Laboratory (GTL) along with heat transfer measurements for film-cooled airfoils in a single-stage high-pressure transonic turbine operating at design corrected conditions. Double-sided heat flux gauges are a critical part of turbine cooling studies, and the new generation improves upon the durability and stability of previous designs, while also introducing high-density layouts that provide better spatial resolution. These new customizable high-density double-sided heat flux gauges allow for multiple heat transfer measurements in a small geometric area such as immediately downstream of a row of cooling holes on an airfoil. Two high-density designs are utilized: Type A consists of 9 gauges laid out within a 5 mm by 2.6 mm (0.20 inch by 0.10 inch) area on the pressure surface of an airfoil, and Type B consists of 7 gauges located at points of predicted interest on the suction surface. At the same time, improvements to the manufacturing and installation processes for single gauges increased the survival rate of the gauges from 47% to 84%.Both individual and high-density heat flux gauges are installed on the blades of a transonic turbine experiment for the second build of the High-Pressure Turbine Innovative Cooling program (HPTIC2). Run in a short duration facility, the single-stage high-pressure turbine operated at design-corrected conditions (matching corrected speed, flow function, and pressure ratio) with forward and aft purge flow and film-cooled blades. Gauges are placed at repeated locations across different cooling schemes in a rainbow rotor configuration. Airfoil film-cooling schemes include round, fan, and advanced shaped cooling holes in addition to uncooled airfoils. Both the pressure and suction surfaces of the airfoils are instrumented at multiple wetted distance locations and percent spans from roughly 10% to 90%. Results from these tests are presented as both time-average values and time-accurate ensemble averages in order to capture unsteady motion and heat transfer distribution created by strong secondary flows and cooling flows.Temperature and Stanton number measurements from a baseline high temperature run with nominal cooling conditions are presented. A comparative analysis of time-average Stanton number across the various cooling schemes shows that no single cooling hole shape performs universally better than its counterparts. Rather, cooling benefits seen through a reduction of Stanton number vary among cooling schemes with changing span and wetted distance. This local variation of cooling benefits is even seen downstream of a single row of holes. Time-average heat transfer is presented for a Type A high-density gauge downstream of a row of fan-shaped cooling holes on the airfoil pressure surface. Results show Stanton number highest near the cooling holes and decreasing with increasing distance from the holes. This trend is explained by the radial migration of cooling flow as it exits the cooling hole. The gauge closest to the cooling hole is therefore exposed to the hot mainstream gas, imparting a large amount of heat to this location on the airfoil surface. A time-average temperature analysis at various experimental time windows gives confidence to the heat flux gauge results. A time-accurate Stanton number analysis is subsequently presented to paint a complete picture of heat transfer at this location on the airfoil pressure surface. Fluctuations in Stanton number reveal secondary peaks in the side-band gauges as the rotor passes through the low temperature vane wakes. This behavior suggests cooling flow unsteadiness as the cooling tracks move to uncover the side-band gauges. The shift in cooling track exposes them to the higher temperature mainstream gas and results in an increase in Stanton number. 2021-10-06 English text The Ohio State University / OhioLINK http://rave.ohiolink.edu/etdc/view?acc_num=osu1608551902273547 http://rave.ohiolink.edu/etdc/view?acc_num=osu1608551902273547 unrestricted This thesis or dissertation is protected by copyright: all rights reserved. It may not be copied or redistributed beyond the terms of applicable copyright laws. |