Fuel flexibility of a multi-staged prototype gas turbine burner
(2017) ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition, GT 2017 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.
(Less)
- author
- Kundu, Atanu LU ; Klingmann, Jens LU ; Subash, Arman Ahamed LU and Collin, Robert LU
- organization
- publishing date
- 2017
- type
- Chapter in Book/Report/Conference proceeding
- publication status
- published
- subject
- host publication
- ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition : Volume 4B: Combustion, Fuels and Emissions - Volume 4B: Combustion, Fuels and Emissions
- volume
- Part F130041-4B
- article number
- GT2017-64782
- pages
- 15 pages
- publisher
- American Society Of Mechanical Engineers (ASME)
- conference name
- ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition, GT 2017
- conference location
- Charlotte, United States
- conference dates
- 2017-06-26 - 2017-06-30
- 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
- 2022-04-25 03:25:31
@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 : Volume 4B: Combustion, Fuels and Emissions}},
isbn = {{9780791850855}},
language = {{eng}},
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}},
doi = {{10.1115/GT2017-64782}},
volume = {{Part F130041-4B}},
year = {{2017}},
}