Zobrazeno 1 - 10
of 102
pro vyhledávání: '"L. Fottner"'
Publikováno v:
Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy. 217:349-356
Detailed experimental and numerical investigations of the flowfield and boundary layer on a highly loaded transonic compressor cascade were performed at various Mach and Reynolds numbers representative of real turbomachinery conditions. The emerging
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::1045b48bdcbc0e8826723a98667e5a9f
https://doi.org/10.1243/095765003322315405
https://doi.org/10.1243/095765003322315405
Autor:
T. Hilderbrandt, L. Fottner
Publikováno v:
Journal of Turbomachinery. 121:709-716
A thorough numerical study was conducted to simulate the flow field inside a highly loaded linear turbine cascade. The numerical investigation was focused on the secondary flow field as well as on the prediction of the overall design goals within rea
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::4e20a81692bcd48578d4e56d6348cd11
https://doi.org/10.1115/1.2836724
https://doi.org/10.1115/1.2836724
Autor:
L. Fottner, A. Duden
Publikováno v:
Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy. 211:309-320
The meridional divergence of low-pressure turbines has a strong influence on their secondary flow field. This paper describes experimental and numerical investigations on two highly loaded linear turbine cascades with the same blade profile and stack
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::015ca03919089b025f4de7647c6ac5e7
https://doi.org/10.1177/095765099721100401
https://doi.org/10.1177/095765099721100401
Publikováno v:
Journal of Turbomachinery. 118:81-87
New blading concepts as used in modern transonic axial-flow compressors require improved loss and deviation angle correlations. The new model presented in this paper incorporates several elements and treats blade-row flows having subsonic and superso
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::7df3f70213074724e996283faaa1a44f
https://doi.org/10.1115/1.2836610
https://doi.org/10.1115/1.2836610
Autor:
L. Fottner, A. P. Weiss
Publikováno v:
Journal of Turbomachinery. 117:133-141
This paper describes an experimental study of the three-dimensional flow within two highly loaded turbine cascades subjected to the same overall load but different load distributions. Data were obtained using pneumatic probes, pressure tappings, and
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::8bc9a9b09fa3ba61e74073295fbac012
https://doi.org/10.1115/1.2835631
https://doi.org/10.1115/1.2835631
Autor:
L. Fottner, T. Herpel
Publikováno v:
International Congress on Instrumentation in Aerospace Simulation Facilities.
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::6659bd76069691b5f2776111d6a4854d
https://doi.org/10.1109/iciasf.1993.687668
https://doi.org/10.1109/iciasf.1993.687668
Autor:
B. Hoss, L. Fottner
Publikováno v:
ICIASF'97 Record. International Congress on Instrumentation in Aerospace Simulation Facilities.
In the past decade great efforts have been undertaken to understand and control the flow structure in a compressor working close to its stability limit. Most of this research work was done at low-speed compressors in isolated test rig facilities. Thi
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::41d991eea6b717a2b5cee32ba4be502f
https://doi.org/10.1109/iciasf.1997.644672
https://doi.org/10.1109/iciasf.1997.644672
Publikováno v:
Volume 5: Turbo Expo 2002, Parts A and B.
Endwall contouring is successfully applied to compressor rotors to reduce boundary layer loading and to control endwall flow. Over-speeds resulting from large relative thickness and curvature of the rotor root section are compensated by the increase
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::7130d90a31de527fc5c2462521e7f361
https://doi.org/10.1115/gt2002-30440
https://doi.org/10.1115/gt2002-30440
Autor:
L. Hilgenfeld, L. Fottner
An experimental study of the turbulent boundary layer was carried out in a highly loaded transonic compressor cascade at various Mach- and Reynolds numbers representative for real turbomachinery conditions. The emerging shock system interacts with th
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::01c22d7199d8a0bbbca11c9953d141c0
https://doi.org/10.1016/b978-008044114-6/50075-2
https://doi.org/10.1016/b978-008044114-6/50075-2
Publikováno v:
Notes on Numerical Fluid Mechanics (NNFM) ISBN: 9783663109037
The boundary layer transition process on compressor blades in a multi-row environment is mainly influenced by incoming periodic wakes generated by the upstream blade row. To simulate such conditions experimentally, a moving bar wake generator device
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::938f14cc01222a42a380c46fba34954f
https://doi.org/10.1007/978-3-663-10901-3_61
https://doi.org/10.1007/978-3-663-10901-3_61