Details
| Original language | English |
|---|---|
| Title of host publication | Ceramics; Controls, Diagnostics and Instrumentation; Education; Manufacturing Materials and Metallurgy |
| Subtitle of host publication | Turbomachinery Technical Conference and Exposition, GT2016, June 13 – 17, 2016, Seoul, South Korea |
| Publisher | American Society of Mechanical Engineers(ASME) |
| ISBN (electronic) | 9780791849828 |
| ISBN (print) | 978-0-7918-4982-8 |
| Publication status | Published - 2016 |
| Event | ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition, GT 2016 - Seoul, Korea, Republic of Duration: 13 Jun 2016 → 17 Jun 2016 |
Publication series
| Name | Proceedings of the ASME Turbo Expo |
|---|---|
| Volume | 6 |
Abstract
Defects in combustion chambers of aircraft engines might have an impact on the reliability of the downstream turbine and the machinés performance. Detecting failures in the combustion chamber of an aircraft engine during operation may improve the resource management and the availability of the system. Aim of the ongoing research project is to find an approach to evaluate the state of the jet engine by analyzing the temperature and emissions field in the exhaust jet. This investigation is part of the collaborative research center SFB 871. The SFB 871 deals with the improvement of the regeneration process of complex capital goods such as aircraft engines. Maintenance, repair, and overhaul processes would be more efficient if the internal status of the engine would be known while still on the wing before it is disassembled. The feasibility of this approach is investigated for a pilot scaled model combustor, which provides optical access and allows the selection of "defined errors" in the combustor. It consists of an atmospheric tubular combustor with an array of eight premixed swirl burners with a maximum output of 160 kW. The operating conditions of one of the eight burners concerning power and air-fuel ratio, can be controlled. A power distribution between the burners is typical fault in an aircraft combustor and will be investigated in this study. It is observed that it is possible to determine small deviations by measuring density profiles applying a tomographic background-oriented schlieren (BOS) technique behind the combustor. Additionally, particle image velocimetry is used to measure differences in the velocity field of the exhaust gases. This study shows that a minimum power deviation of one burner in an array of a total of eight burners is detectable in the exhaust plane with the above mentioned measurement techniques.
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Ceramics; Controls, Diagnostics and Instrumentation; Education; Manufacturing Materials and Metallurgy: Turbomachinery Technical Conference and Exposition, GT2016, June 13 – 17, 2016, Seoul, South Korea. American Society of Mechanical Engineers(ASME), 2016. (Proceedings of the ASME Turbo Expo; Vol. 6).
Research output: Chapter in book/report/conference proceeding › Conference contribution › Research › peer review
}
TY - GEN
T1 - Defect detection in an annular swirl-burner-Array by optical measuring exhaust gases
AU - von der Haar, Henrik
AU - Hartmann, Ulrich
AU - Hennecke, Christoph
AU - Dinkelacker, Friedrich
AU - Seume, Jörg Reinhart
N1 - Publisher Copyright: Copyright © 2016 by ASME.
PY - 2016
Y1 - 2016
N2 - Defects in combustion chambers of aircraft engines might have an impact on the reliability of the downstream turbine and the machinés performance. Detecting failures in the combustion chamber of an aircraft engine during operation may improve the resource management and the availability of the system. Aim of the ongoing research project is to find an approach to evaluate the state of the jet engine by analyzing the temperature and emissions field in the exhaust jet. This investigation is part of the collaborative research center SFB 871. The SFB 871 deals with the improvement of the regeneration process of complex capital goods such as aircraft engines. Maintenance, repair, and overhaul processes would be more efficient if the internal status of the engine would be known while still on the wing before it is disassembled. The feasibility of this approach is investigated for a pilot scaled model combustor, which provides optical access and allows the selection of "defined errors" in the combustor. It consists of an atmospheric tubular combustor with an array of eight premixed swirl burners with a maximum output of 160 kW. The operating conditions of one of the eight burners concerning power and air-fuel ratio, can be controlled. A power distribution between the burners is typical fault in an aircraft combustor and will be investigated in this study. It is observed that it is possible to determine small deviations by measuring density profiles applying a tomographic background-oriented schlieren (BOS) technique behind the combustor. Additionally, particle image velocimetry is used to measure differences in the velocity field of the exhaust gases. This study shows that a minimum power deviation of one burner in an array of a total of eight burners is detectable in the exhaust plane with the above mentioned measurement techniques.
AB - Defects in combustion chambers of aircraft engines might have an impact on the reliability of the downstream turbine and the machinés performance. Detecting failures in the combustion chamber of an aircraft engine during operation may improve the resource management and the availability of the system. Aim of the ongoing research project is to find an approach to evaluate the state of the jet engine by analyzing the temperature and emissions field in the exhaust jet. This investigation is part of the collaborative research center SFB 871. The SFB 871 deals with the improvement of the regeneration process of complex capital goods such as aircraft engines. Maintenance, repair, and overhaul processes would be more efficient if the internal status of the engine would be known while still on the wing before it is disassembled. The feasibility of this approach is investigated for a pilot scaled model combustor, which provides optical access and allows the selection of "defined errors" in the combustor. It consists of an atmospheric tubular combustor with an array of eight premixed swirl burners with a maximum output of 160 kW. The operating conditions of one of the eight burners concerning power and air-fuel ratio, can be controlled. A power distribution between the burners is typical fault in an aircraft combustor and will be investigated in this study. It is observed that it is possible to determine small deviations by measuring density profiles applying a tomographic background-oriented schlieren (BOS) technique behind the combustor. Additionally, particle image velocimetry is used to measure differences in the velocity field of the exhaust gases. This study shows that a minimum power deviation of one burner in an array of a total of eight burners is detectable in the exhaust plane with the above mentioned measurement techniques.
UR - http://www.scopus.com/inward/record.url?scp=84991227726&partnerID=8YFLogxK
U2 - 10.1115/gt2016-57847
DO - 10.1115/gt2016-57847
M3 - Conference contribution
SN - 978-0-7918-4982-8
T3 - Proceedings of the ASME Turbo Expo
BT - Ceramics; Controls, Diagnostics and Instrumentation; Education; Manufacturing Materials and Metallurgy
PB - American Society of Mechanical Engineers(ASME)
T2 - ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition, GT 2016
Y2 - 13 June 2016 through 17 June 2016
ER -