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research-article

Flow Field and Wall Temperature Measurements for Reacting Flow in a Lean Premixed Swirl Stabilized Can Combustor

[+] Author and Article Information
Suhyeon Park

Advanced Propulsion and Power Laboratory, Department of Mechanical Engineering, Virginia Tech, Blacksburg, VA (US) 24061
suhyeon.park@vt.edu

David Gomez Ramirez

Advanced Propulsion and Power Laboratory Department of Mechanical Engineering, Virginia Tech, Blacksburg, VA (US) 24061
gomezd@vt.edu

Siddhartha Gadiraju

Advanced Propulsion and Power Laboratory Department of Mechanical Engineering, Virginia Tech, Blacksburg, VA (US) 24061
siddhu@vt.edu

Sandeep Kedukodi

Advanced Propulsion and Power Laboratory Department of Mechanical Engineering, Virginia Tech, Blacksburg, VA (US) 24061
ksandeep@vt.edu

Srinath V. Ekkad

Advanced Propulsion and Power Laboratory, Department of Mechanical Engineering, Virginia Tech, Blacksburg, VA (US) 24061
sekkad@ncsu.edu

Hee Koo Moon

Solar Turbine Inc. San Diego, California, USA
heekoomoon@gmail.com

Yong Kim

Solar Turbine Inc. San Diego, California, USA
KIM_YONG_W@solarturbines.com

Ram Srinivasan

Solar Turbine Inc. San Diego, California, USA
Srinivasan_Ram@solarturbines.com

1Corresponding author.

ASME doi:10.1115/1.4039462 History: Received November 08, 2017; Revised December 30, 2017

Abstract

In this study, we provide detailed wall heat flux measurements and flow details for reacting flow conditions in a model combustor. Heat transfer measurements inside a gas turbine combustor provides one of the most serious challenges for gas turbine researchers. Gas turbine combustor improvements require accurate measurement and prediction of reacting flows. Flow and heat transfer measurements inside combustors under reacting flow conditions remains a challenge. The mechanisms of thermal energy transfer must be investigated by studying the flow characteristics and associated heat load. This paper experimentally investigates the effects of combustor operating conditions on the reacting flow in an optical single can combustor. The swirling flow was generated by an industrial lean pre-mixed, axial swirl fuel nozzle. Planar particle image velocimetry (PIV) data were analyzed to understand the characteristics of the flow field. Liner surface temperatures were measured in reacting condition with an infrared camera for a single case. Experiments were conducted at Reynolds numbers ranging between 50000 and 110000 (with respect to the nozzle diameter, D_N); equivalence ratios between 0.55 and 0.78; and pilot fuel split ratios of 0 to 6%. Characterizing the impingement location on the liner, and the turbulent kinetic energy (TKE) distribution were a fundamental part of the investigation. Self-similar characteristics were observed at different reacting conditions. Swirling exit flow from the nozzle was found to be unaffected by the operating conditions with little effect on the liner. Comparison between reacting and non-reacting flows yielded very interesting and striking differences.

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