Imperial College London
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DrSinaStapelfeldt

Faculty of Engineering, Department of Mechanical Engineering

Lecturer
 
 
 
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Contact

 

+44 (0)20 7594 7076s.stapelfeldt

 
 
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Assistant

 

Mr Peter Higgs +44 (0)20 7594 7078

 
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Location

 

556City and Guilds BuildingSouth Kensington Campus

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Summary

 

Publications

Citation

BibTex format

@article{Hill:2022:10.3390/ijtpp7010007,
author = {Hill, G and Gambel, J and Schneider, S and Peitsch, D and Stapelfeldt, S},
doi = {10.3390/ijtpp7010007},
journal = {International Journal of Turbomachinery, Propulsion and Power},
pages = {1--16},
title = {Aeroelastic stability of combined plunge-pitch mode shapes in a linear compressor cascade},
url = {http://dx.doi.org/10.3390/ijtpp7010007},
volume = {7},
year = {2022}
}
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RIS format (EndNote, RefMan)

TY  - JOUR
AB  - Modern aeroengine designs strive for peak specific fuel and thermal efficiency. To achieve these goals, engines have more highly loaded compressor stages, thinner aerofoils, and blended titanium integrated disks (blisks) to reduce weight. These configurations promote the occurrence of aeroelastic phenomena such as flutter. Two important parameters known to influence flutter stability are the reduced frequency and the ratio of plunge and pitch components in a combined flap mode shape. These are used as design criteria in the engine development process. However, the limit of these criteria is not fully understood. The following research aims to bridge the gap between semi-analytical models and modern compressors by systematically investigating the flutter stability of a linear compressor cascade. This paper introduces the plunge-to-pitch incidence ratio, which is defined as a function of reduced frequency and pitch axis setback for a first flap (1F) mode shape. Using numerical simulations, in addition to experimental validation, aerodynamic damping is computed for many modes to build stability maps. The results confirm the importance of these two parameters in compressor aeroelastic stability as well as demonstrate the significance of the plunge-to-pitch incidence ratio for predicting the flutter limit.
AU  - Hill,G
AU  - Gambel,J
AU  - Schneider,S
AU  - Peitsch,D
AU  - Stapelfeldt,S
DO  - 10.3390/ijtpp7010007
EP  - 16
PY  - 2022///
SN  - 2504-186X
SP  - 1
TI  - Aeroelastic stability of combined plunge-pitch mode shapes in a linear compressor cascade
T2  - International Journal of Turbomachinery, Propulsion and Power
UR  - http://dx.doi.org/10.3390/ijtpp7010007
UR  - https://www.mdpi.com/2504-186X/7/1/7
UR  - http://hdl.handle.net/10044/1/95876
VL  - 7
ER  -
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