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The Experimental Studies of Improving the Aerodynamic Performance of a Turbine Exhaust System

[+] Author Affiliations
Stephen Guillot, Wing F. Ng

Techsburg, Inc., Christiansburg, VA

Hans D. Hamm, Ulrich E. Stang

Solar Turbines, Inc., San Diego, CA

Kevin T. Lowe

Virginia Tech, Blacksburg, VA

Paper No. GT2014-25481, pp. V01BT27A012; 17 pages
doi:10.1115/GT2014-25481
From:
  • ASME Turbo Expo 2014: Turbine Technical Conference and Exposition
  • Volume 1B: Marine; Microturbines, Turbochargers and Small Turbomachines; Steam Turbines
  • Düsseldorf, Germany, June 16–20, 2014
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-4558-5
  • Copyright © 2014 by Solar Turbines Incorporated

abstract

Analysis and testing was conducted to optimize an axial diffuser-collector gas turbine exhaust. Two subsonic wind tunnel facilities were designed and built to support this program. A 1/12th scale test rig enabled rapid and efficient evaluation of multiple geometries. This test facility was designed to run continuously at an inlet Mach number of 0.41 and an inlet hydraulic diameter-based Reynolds number of 3.4 × 105. A 1/4th geometric scale test rig was designed and built to validate the data in the 1/12th scale rig. This blow-down rig facilitated testing at a nominally equivalent inlet Mach number, while the Reynolds number was matched to realistic engine conditions via back pressure. Multi-hole pneumatic pressure probes, particle image velocimetry and surface oil flow visualization was deployed in conjunction with computational tools to explore physics-based alterations to the exhaust geometry. The design modifications resulted in a substantial increase in the overall pressure recovery coefficient of +0.07 (experimental result) above the baseline geometry. The optimized performance, first measured at 1/12th scale and obtained using CFD was validated at the full scale Reynolds number.

Copyright © 2014 by Solar Turbines Incorporated

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