Details
| Original language | English |
|---|---|
| Title of host publication | Turbomachinery |
| Publisher | American Society of Mechanical Engineers(ASME) |
| ISBN (electronic) | 9780791849705 |
| Publication status | Published - 1 Jan 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 | 2B-2016 |
Abstract
The present work numerically investigates the influences that four defects in the hot gas path of a civil aircraft engine have on the density distribution of the exhaust jet. The defects detectability with tomographic measurements using the Background-oriented schlieren method (BOS) is evaluated in order to draw conclusions on the condition of the engine before disassembly. The modeled defects are: The variation of the radial gap between the rotor blade tip and the casing in the second stage of a high-pressure turbine (HPT), the burning of the trailing edge of the stator vanes and rotor blades of the second stage of the HPT, the variation of the cooling air mass flow in the first stage of the HPT, and the variation of the temperature at the outlet of the combustion chamber. Synthetic measurements show that a characteristic signature at the outer border of the core mass flow in the exhaust jet can be measured with BOS when the radial gap is varied. However, the burning of the trailing edges cannot be detected. The variation of the cooling air massflow affects the entire density distribution and can be measured with BOS. Defects of the burner nozzles affect a larger local area of the exhaust jet and thus can also clearly be identified with BOS. The results show that different defects in the hot gas path result in characteristic signatures in the density distribution of the exhaust jet and that they can be measured with BOS. It is thus possible to detect defects in the hot gas path with BOS before the disassembly of the engine.
ASJC Scopus subject areas
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Turbomachinery. American Society of Mechanical Engineers(ASME), 2016. (Proceedings of the ASME Turbo Expo; Vol. 2B-2016).
Research output: Chapter in book/report/conference proceeding › Conference contribution › Research › peer review
}
TY - GEN
T1 - Numerical evaluation of the condition of a jet engine through exhaust jet analysis
AU - Adamczuk, Rafael R.
AU - Seume, Joerg R.
PY - 2016/1/1
Y1 - 2016/1/1
N2 - The present work numerically investigates the influences that four defects in the hot gas path of a civil aircraft engine have on the density distribution of the exhaust jet. The defects detectability with tomographic measurements using the Background-oriented schlieren method (BOS) is evaluated in order to draw conclusions on the condition of the engine before disassembly. The modeled defects are: The variation of the radial gap between the rotor blade tip and the casing in the second stage of a high-pressure turbine (HPT), the burning of the trailing edge of the stator vanes and rotor blades of the second stage of the HPT, the variation of the cooling air mass flow in the first stage of the HPT, and the variation of the temperature at the outlet of the combustion chamber. Synthetic measurements show that a characteristic signature at the outer border of the core mass flow in the exhaust jet can be measured with BOS when the radial gap is varied. However, the burning of the trailing edges cannot be detected. The variation of the cooling air massflow affects the entire density distribution and can be measured with BOS. Defects of the burner nozzles affect a larger local area of the exhaust jet and thus can also clearly be identified with BOS. The results show that different defects in the hot gas path result in characteristic signatures in the density distribution of the exhaust jet and that they can be measured with BOS. It is thus possible to detect defects in the hot gas path with BOS before the disassembly of the engine.
AB - The present work numerically investigates the influences that four defects in the hot gas path of a civil aircraft engine have on the density distribution of the exhaust jet. The defects detectability with tomographic measurements using the Background-oriented schlieren method (BOS) is evaluated in order to draw conclusions on the condition of the engine before disassembly. The modeled defects are: The variation of the radial gap between the rotor blade tip and the casing in the second stage of a high-pressure turbine (HPT), the burning of the trailing edge of the stator vanes and rotor blades of the second stage of the HPT, the variation of the cooling air mass flow in the first stage of the HPT, and the variation of the temperature at the outlet of the combustion chamber. Synthetic measurements show that a characteristic signature at the outer border of the core mass flow in the exhaust jet can be measured with BOS when the radial gap is varied. However, the burning of the trailing edges cannot be detected. The variation of the cooling air massflow affects the entire density distribution and can be measured with BOS. Defects of the burner nozzles affect a larger local area of the exhaust jet and thus can also clearly be identified with BOS. The results show that different defects in the hot gas path result in characteristic signatures in the density distribution of the exhaust jet and that they can be measured with BOS. It is thus possible to detect defects in the hot gas path with BOS before the disassembly of the engine.
UR - http://www.scopus.com/inward/record.url?scp=84991832962&partnerID=8YFLogxK
U2 - 10.1115/GT2016-6947
DO - 10.1115/GT2016-6947
M3 - Conference contribution
AN - SCOPUS:84991832962
T3 - Proceedings of the ASME Turbo Expo
BT - Turbomachinery
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 -