Zobrazeno 1 - 10
of 68
pro vyhledávání: '"H. Starken"'
Autor:
W. Steinert, H. Starken
The design of modern axial flow compressor blade sections as well as the code validation require experimental information about the transition and separation behavior of blade surface boundary layers. The experience has shown in the past that such in
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::be6437bf525920d8d98c05baf488c309
https://elib.dlr.de/38281/
https://elib.dlr.de/38281/
A transonic compressor rotor cascade designed for an inlet Mach number of 1.09 and 14 degrees of flow turning has been redesigned for higher loading by an increased pitch-to-chord ratio. Test results, showing the influence of inlet Mach number and fl
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::d75b3501291ee4f4d521dc3822115be9
https://elib.dlr.de/37877/
https://elib.dlr.de/37877/
Tests of transonic compressor cascades require special measuring techniques to determine the inlet flow angle around sonic inlet flow conditions. One of the main requirements for these methods is the ability to adjust the inlet flow angle during the
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::b967a64ddea857eeb90024de905ea464
https://elib.dlr.de/37794/
https://elib.dlr.de/37794/
Autor:
H. Starken, H. A. Schreiber
Experiments have been performed in a Supersonic cascade facility to elucidate the fluid dynamic phenomena and loss mechanism of a strong shock-wave turbulent boundary layer interaction in a compressor cascade. The cascade geometry is typical for a tr
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::78598d8762bd9fce6cd1e15e4a10dbbd
https://elib.dlr.de/37793/
https://elib.dlr.de/37793/
Similar to jet engine development, modern design methods are used today to improve the performance of industrial compressors. In order to verify the loading limits, a cascade profile representative for the first rotor hub section of an industrial com
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::15464f09d52915788f667a4be325961b
https://elib.dlr.de/37749/
https://elib.dlr.de/37749/
Publikováno v:
Volume 1: Turbomachinery.
Efforts to reduce the specific fuel consumption of a modern aero engine focus in particular on increasing the by-pass ratio beyond the current level of around 5. One concept is the counterrotating shrouded propfan operating at low overall pressure ra
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::6acbd4f90f64e2e5cbf855d18c0c8131
https://doi.org/10.1115/91-gt-335
https://doi.org/10.1115/91-gt-335
Autor:
H. Starken, H. A. Schreiber
Publikováno v:
Journal of Turbomachinery. 114:503-503
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::2374ea1ebb954322858b95b66afc8760
https://doi.org/10.1115/1.2929172
https://doi.org/10.1115/1.2929172
Publikováno v:
Journal of Engineering for Gas Turbines and Power. 106:279-287
In order to verify a new controlled diffusion blade design concept, the stator of an existing transonic axial compressor stage was redesigned. Stator and equivalent cascade tests revealed the potential of such blades for a considerably higher aerodyn
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::398df9727441c3a9e2aabe3ea0c1f551
https://doi.org/10.1115/1.3239560
https://doi.org/10.1115/1.3239560
Autor:
H.-J. Lichtfuss, H. Starken
Publikováno v:
Progress in Aerospace Sciences. 15:37-149
This report gives a survey of the inviscid supersonic flow through a straight lattice row. The main subject of this paper is dedicated to the supersonic inlet and outlet flow at such a cascade. It is shown that the cascade flow behaviour is altered r
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::8445b266e9893117837826fd4dea8552
https://doi.org/10.1016/0376-0421(74)90004-9
https://doi.org/10.1016/0376-0421(74)90004-9
Publikováno v:
Journal of Turbomachinery. 110:456-466
Results are presented from an experimental investigation of a linear, supersonic, compressor cascade tested in the supersonic cascade wind tunnel facility at the DFVLR in Cologne, Federal Republic of Germany. The cascade design was derived from the n
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::df9cc3fb8551e12128a300b74093aa4f
https://doi.org/10.1115/1.3262219
https://doi.org/10.1115/1.3262219