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research-article

DESIGN OF THE PURDUE EXPERIMENTAL TURBINE AEROTHERMAL LABORATORY FOR OPTICAL AND SURFACE AERO-THERMAL MEASUREMENTS

[+] Author and Article Information
Guillermo Paniagua

Purdue University, West Lafayette, Indiana, United States
gpaniagua@me.com

David Gonzalez Cuadrado

Purdue University, West Lafayette, Indiana, United States
gonza279@purdue.edu

Jorge Saavedra

Purdue University, West Lafayette, Indiana, United States
saavedra@purdue.edu

Valeria Andreoli

Purdue University, West Lafayette, Indiana, United States
vandreol@purdue.edu

Terrence Meyer

Purdue University, West Lafayette, Indiana, United States
trmeyer@purdue.edu

Juan P. Solano

Universidad Politécnica de Cartagena, Cartagena, Murcia, Spain
juanp.solano@upct.es

Ruth Herrero

Universidad Politécnica de Cartagena, Cartagena, Murcia, Spain
ruth.herrero@upct.es

Scott E. Meyer

Purdue University, West Lafayette, Indiana, United States
meyerse@purdue.edu

David Lawrence

Aerodyn Engineering Inc., Indianapolis, Indiana, United States
dlawrence@aerodyneng.com

1Corresponding author.

ASME doi:10.1115/1.4040683 History: Received April 15, 2018; Revised June 23, 2018

Abstract

Following three decades of research in short duration facilities, Purdue University has developed an alternative turbine facility in view of the modern technology in computational fluid mechanics, structural analysis, manufacturing, heating, control and electronics. The proposed turbine facility can operate continuously and also perform transients, suited for precise heat flux, efficiency and optical measurement techniques to advance turbine aero-thermo-structural engineering. The facility has two different test sections, linear and annular, to service both fundamental and applied research. The linear test section is completely transparent for optical imaging and spectroscopy, aimed at technology readiness levels (TRLs) of 1 to 2. The annular test section was designed with optical access to perform proof of concepts as well as validation of turbine component performance for relevant non-dimensional parameters at TRLs of 3 to 4. The large mass flow rate (28 kg/s) combined with a minimum hub to tip ratio of 0.85 allows high spatial resolution. The Reynolds number (Re) extends from 60,000 to 3,000,000, based on the vane outlet flow properties with an axial chord of 0.06 m and a turning angle of 72 deg. The pressure ratio can be independently adjusted, enabling testing from low subsonic to Mach 3.2. The test duration can range from milliseconds to minutes. This manuscript provides a detailed description of the sequential design methodology from zero-dimensional to three-dimensional unsteady analysis as well as of the measurement techniques available in this turbine facility.

Copyright (c) 2018 by ASME
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