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Fuel flexibility of a multi-staged prototype gas turbine burner

Kundu, Atanu LU ; Klingmann, Jens LU ; Subash, Arman Ahamed LU and Collin, Robert LU (2017) ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition, GT 2017 In ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition Part F130041-4B.
Abstract

Gas turbines are widely used power generation equipment and very important for its efficiency and flexible operability. With the increasing demand of low carbon or less greenhouse gas emission from gas turbine, usage of clean fuel (i.e. hydrogen) is highly recommended. Adaptation with various type of fuels without any operability issues are the primary focus of interest while design and development of a low NOx gas turbine combustion system. Due to chemical and physical property variation of different fuel, a common combustion system design is complex and require extensive testing. The present paper is focused on fuel flexibility of an industrial prototype burner, designed and manufactured by Siemens Industrial Turbomachinery AB,... (More)

Gas turbines are widely used power generation equipment and very important for its efficiency and flexible operability. With the increasing demand of low carbon or less greenhouse gas emission from gas turbine, usage of clean fuel (i.e. hydrogen) is highly recommended. Adaptation with various type of fuels without any operability issues are the primary focus of interest while design and development of a low NOx gas turbine combustion system. Due to chemical and physical property variation of different fuel, a common combustion system design is complex and require extensive testing. The present paper is focused on fuel flexibility of an industrial prototype burner, designed and manufactured by Siemens Industrial Turbomachinery AB, Sweden. In this work, a baseline case (Methane fuel) is compared with different custom fuel blends (mixture of methane with natural gas and hydrogen). The primary and secondary combustion characteristics were modified when hydrogen blended fuels were introduced. The Lean Blowout limit was extended for the primary and secondary flames. The secondary flame macro structure was captured using Planar Laser Induced Fluorescence and natural luminosity imaging; whereas primary flame location was characterized by the thermocouple readings. Operational stability map and emission (NOx and CO) capability of the burner was determined from the experiment. Numerical calculation using ANSYS FLUENT was performed to simulate the combustion process and compare the results with experiment. The experimental and simulation effort provided information about the flame macrostructure and operability (lean operability limit was extended by 100 K) of the new technology burner when the combustion system was exposed to different type of fuels.

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author
organization
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type
Chapter in Book/Report/Conference proceeding
publication status
published
subject
in
ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition
volume
Part F130041-4B
pages
15 pages
publisher
American Society Of Mechanical Engineers (ASME)
conference name
ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition, GT 2017
external identifiers
  • scopus:85029033433
ISBN
9780791850855
DOI
10.1115/GT2017-64782
language
English
LU publication?
yes
id
365265c8-9043-4d14-b2df-88fbbae3d436
date added to LUP
2017-10-22 08:53:12
date last changed
2018-01-07 12:23:20
@inproceedings{365265c8-9043-4d14-b2df-88fbbae3d436,
  abstract     = {<p>Gas turbines are widely used power generation equipment and very important for its efficiency and flexible operability. With the increasing demand of low carbon or less greenhouse gas emission from gas turbine, usage of clean fuel (i.e. hydrogen) is highly recommended. Adaptation with various type of fuels without any operability issues are the primary focus of interest while design and development of a low NOx gas turbine combustion system. Due to chemical and physical property variation of different fuel, a common combustion system design is complex and require extensive testing. The present paper is focused on fuel flexibility of an industrial prototype burner, designed and manufactured by Siemens Industrial Turbomachinery AB, Sweden. In this work, a baseline case (Methane fuel) is compared with different custom fuel blends (mixture of methane with natural gas and hydrogen). The primary and secondary combustion characteristics were modified when hydrogen blended fuels were introduced. The Lean Blowout limit was extended for the primary and secondary flames. The secondary flame macro structure was captured using Planar Laser Induced Fluorescence and natural luminosity imaging; whereas primary flame location was characterized by the thermocouple readings. Operational stability map and emission (NOx and CO) capability of the burner was determined from the experiment. Numerical calculation using ANSYS FLUENT was performed to simulate the combustion process and compare the results with experiment. The experimental and simulation effort provided information about the flame macrostructure and operability (lean operability limit was extended by 100 K) of the new technology burner when the combustion system was exposed to different type of fuels.</p>},
  author       = {Kundu, Atanu and Klingmann, Jens and Subash, Arman Ahamed and Collin, Robert},
  booktitle    = {ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition},
  isbn         = {9780791850855},
  language     = {eng},
  pages        = {15},
  publisher    = {American Society Of Mechanical Engineers (ASME)},
  title        = {Fuel flexibility of a multi-staged prototype gas turbine burner},
  url          = {http://dx.doi.org/10.1115/GT2017-64782},
  volume       = {Part F130041-4B},
  year         = {2017},
}