Details
| Original language | English |
|---|---|
| Title of host publication | Structures and Dynamics |
| Publisher | American Society of Mechanical Engineers(ASME) |
| ISBN (electronic) | 9780791850930 |
| Publication status | Published - 2017 |
| Event | ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition, GT 2017 - Charlotte, United States Duration: 26 Jun 2017 → 30 Jun 2017 |
Publication series
| Name | Proceedings of the ASME Turbo Expo |
|---|---|
| Volume | 7B-2017 |
Abstract
Impacts of foreign objects can cause cracks and dents in airfoils, especially in the leading edge. The regeneration of highpressure compressors blisks with current repair methods is often restricted to a local blending of these edges. This can cause significant changes in the airfoils' geometrical properties, which in turn influence their aerodynamic and aeroelastic characteristics. Changes at the leading edge have a particularly strong influence on the airfoils' aerodynamic properties. In order to be able to make an informed decision about if and how a repair should be performed, consequences have to be predicted in advance. To investigate their influence on the aerodynamic and aeroelastic behavior, typical blend repairs are applied to the geometry of a blisk in a 1.5-stage research axial compressor [1], which are representative in shape and size. Blisks (Blade-Integrated-diSK) are function integrated components, which are expected to have a high life span due to significant costs in design and production. Similar modifications are implemented at different radial heights of the blades, in order to investigate the influence of location and penetration depth of blend repairs. It is assured that only the blend repair region is modified while the rest of the blade stays in the original shape. Thus, a realistic change of the geometry is given. The numerical study presented here deals with the influence of geometric imperfections, blend repairs in particular, on the aerodynamic and aeroelastic behavior of the high pressure compressors blisks. Results show that blend repairs have an influence on the local pressure distribution as well as on the local flow turning. Even though the leading edge is reshaped during repair, performance degradation can be observed. Furthermore, the working range of the compressor stage is influenced by the blend-repairs, which is of great importance for safe operation. Finally, the local changes in aerodynamics and blade deformation influence the aeroelastic behavior. This influence depends on the investigated mode shape and the location of the modification. The closer the modification is located towards the tip, the more pronounced are the shifts in aerodynamic damping and aerodynamic stiffness. Low torsional mode shapes display the highest sensitivity to the modifications.
ASJC Scopus subject areas
- Engineering(all)
- General Engineering
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Structures and Dynamics. American Society of Mechanical Engineers(ASME), 2017. (Proceedings of the ASME Turbo Expo; Vol. 7B-2017).
Research output: Chapter in book/report/conference proceeding › Conference contribution › Research › peer review
}
TY - GEN
T1 - Influence of geometric imperfections on aerodynamic and aeroelastic behavior of a compressor blisk
AU - Keller, Christian
AU - Kellersmann, Andreas
AU - Friedrichs, Jens
AU - Seume, Joerg R.
N1 - Funding information: The present work has been carried out in the subprojects C6 and D4 within the Collaborative Research Center 871 ’Regeneration of Complex Capital Goods’, which is funded by the DFG (German Research Foundation) under grant of CRC 871/2. The authors gratefully thank the DLR Institute of Propulsion Technology for the deployment of the numerical solver TRACE.
PY - 2017
Y1 - 2017
N2 - Impacts of foreign objects can cause cracks and dents in airfoils, especially in the leading edge. The regeneration of highpressure compressors blisks with current repair methods is often restricted to a local blending of these edges. This can cause significant changes in the airfoils' geometrical properties, which in turn influence their aerodynamic and aeroelastic characteristics. Changes at the leading edge have a particularly strong influence on the airfoils' aerodynamic properties. In order to be able to make an informed decision about if and how a repair should be performed, consequences have to be predicted in advance. To investigate their influence on the aerodynamic and aeroelastic behavior, typical blend repairs are applied to the geometry of a blisk in a 1.5-stage research axial compressor [1], which are representative in shape and size. Blisks (Blade-Integrated-diSK) are function integrated components, which are expected to have a high life span due to significant costs in design and production. Similar modifications are implemented at different radial heights of the blades, in order to investigate the influence of location and penetration depth of blend repairs. It is assured that only the blend repair region is modified while the rest of the blade stays in the original shape. Thus, a realistic change of the geometry is given. The numerical study presented here deals with the influence of geometric imperfections, blend repairs in particular, on the aerodynamic and aeroelastic behavior of the high pressure compressors blisks. Results show that blend repairs have an influence on the local pressure distribution as well as on the local flow turning. Even though the leading edge is reshaped during repair, performance degradation can be observed. Furthermore, the working range of the compressor stage is influenced by the blend-repairs, which is of great importance for safe operation. Finally, the local changes in aerodynamics and blade deformation influence the aeroelastic behavior. This influence depends on the investigated mode shape and the location of the modification. The closer the modification is located towards the tip, the more pronounced are the shifts in aerodynamic damping and aerodynamic stiffness. Low torsional mode shapes display the highest sensitivity to the modifications.
AB - Impacts of foreign objects can cause cracks and dents in airfoils, especially in the leading edge. The regeneration of highpressure compressors blisks with current repair methods is often restricted to a local blending of these edges. This can cause significant changes in the airfoils' geometrical properties, which in turn influence their aerodynamic and aeroelastic characteristics. Changes at the leading edge have a particularly strong influence on the airfoils' aerodynamic properties. In order to be able to make an informed decision about if and how a repair should be performed, consequences have to be predicted in advance. To investigate their influence on the aerodynamic and aeroelastic behavior, typical blend repairs are applied to the geometry of a blisk in a 1.5-stage research axial compressor [1], which are representative in shape and size. Blisks (Blade-Integrated-diSK) are function integrated components, which are expected to have a high life span due to significant costs in design and production. Similar modifications are implemented at different radial heights of the blades, in order to investigate the influence of location and penetration depth of blend repairs. It is assured that only the blend repair region is modified while the rest of the blade stays in the original shape. Thus, a realistic change of the geometry is given. The numerical study presented here deals with the influence of geometric imperfections, blend repairs in particular, on the aerodynamic and aeroelastic behavior of the high pressure compressors blisks. Results show that blend repairs have an influence on the local pressure distribution as well as on the local flow turning. Even though the leading edge is reshaped during repair, performance degradation can be observed. Furthermore, the working range of the compressor stage is influenced by the blend-repairs, which is of great importance for safe operation. Finally, the local changes in aerodynamics and blade deformation influence the aeroelastic behavior. This influence depends on the investigated mode shape and the location of the modification. The closer the modification is located towards the tip, the more pronounced are the shifts in aerodynamic damping and aerodynamic stiffness. Low torsional mode shapes display the highest sensitivity to the modifications.
UR - http://www.scopus.com/inward/record.url?scp=85029010997&partnerID=8YFLogxK
U2 - 10.1115/gt2017-63556
DO - 10.1115/gt2017-63556
M3 - Conference contribution
AN - SCOPUS:85029010997
T3 - Proceedings of the ASME Turbo Expo
BT - Structures and Dynamics
PB - American Society of Mechanical Engineers(ASME)
T2 - ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition, GT 2017
Y2 - 26 June 2017 through 30 June 2017
ER -