Zobrazeno 1 - 10
of 22
pro vyhledávání: '"Alexander Hergt"'
Autor:
Alexander Hergt, Tobias Danninger, Joachim Klinner, Sebastian Grund, Manfred Beversdorff, Christian Werner-Spatz
Publikováno v:
International Journal of Turbomachinery, Propulsion and Power, Vol 9, Iss 1, p 1 (2024)
In this paper, an experimental and numerical investigation of the effect of leading-edge erosion in transonic blades was performed. The measurements were carried out on a linear blade cascade in the Transonic Cascade Wind Tunnel of DLR in Cologne at
Externí odkaz:
https://doaj.org/article/a73b3111b3f94b6182f9e0054615cc6c
Publikováno v:
International Journal of Turbomachinery, Propulsion and Power, Vol 8, Iss 4, p 47 (2023)
The successful design of compressor blades through numerical optimization relies on accurate CFD-RANS solvers that are able to capture the general performance of a given design candidate. However, this is a difficult task to achieve in transonic flow
Externí odkaz:
https://doaj.org/article/d3252781a938465db10f6e797e2273c1
Publikováno v:
Experiments in Fluids. 62
The dynamics of a transonic buffet flow on the suction side of a highly loaded 2-D compressor blade model is investigated at a chord-based Reynolds number of$$1.4 \times 10^6$$1.4×106and an inlet Mach number of 1.05. Near stall the detached bow shoc
Autor:
Benoît Tartinville, Piotr Kaczyński, Ryszard Szwaba, Charles Hirsch, Alexander Hergt, Michal Piotrowicz, Pawel Flaszynski, Patrick Grothe
Publikováno v:
Notes on Numerical Fluid Mechanics and Multidisciplinary Design ISBN: 9783030474607
In the case of a civil turbofan engine operating at particularly high altitudes the Reynolds number can drop by a factor of 4, when compared to the sea level values. The laminar boundary layer on the transonic compressor rotor blades interacts with s
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::a12d47f99560f5056385128b1969cd85
https://doi.org/10.1007/978-3-030-47461-4_4
https://doi.org/10.1007/978-3-030-47461-4_4
Autor:
Thomas Stürzebecher, Alexander Hergt, Sebastian Grund, Aaron Kasper, Jasmin Flamm, Eberhard Nicke
Publikováno v:
Journal of Physics: Conference Series. 1909:012025
As part of Clean Sky 2 (Engines ITD), a working group, formed by the DLR Institute of Propulsion Technology, MTU Aero Engines and GKN Aerospace, is setting up a complete compression system module (LPC/ICD/HPC). The aim of the project is to shorten th
Autor:
Wolfgang Steinert, Christian Willert, Alexander Hergt, Sebastian Grund, Manfred Beversdorff, Joachim Klinner
The flow through a transonic compressor cascade is characterized by high unsteadiness and a high loss level. This results from the shock waves in the blade cascade and their interaction with the blade suction side boundary layer. In the case of a lam
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::332aa971f4a6126877847c9c4f8f95a8
https://doi.org/10.1115/gt2019-90440
https://doi.org/10.1115/gt2019-90440
Autor:
Alexander Hergt, Manfred Beversdorff, Jens Wellner, Joachim Klinner, Christian Willert, Sebastian Grund, Wolfgang Steinert
Publikováno v:
Journal of Turbomachinery. 141
The flow through a transonic compressor cascade shows a very complex structure due to the occuring shock waves. In addition, the interaction of these shock waves with the blade boundary layer inherently leads to a very unsteady flow behaviour. The ai
Publikováno v:
Experiments in Fluids. 60
The influence of transition control on shock-induced flow separation was investigated in a highly loaded transonic compressor cascade at an inlet Mach number of 1.21 and a chord-based Reynolds number of $$1.4 \times 10^6$$ . Transition was influenced
Autor:
Manfred Beversdorff, Sebastian Grund, Joachim Klinner, Wolfgang Steinert, Alexander Hergt, Ulrich Siller
Publikováno v:
Volume 2A: Turbomachinery.
The development of modern axial compressors has already reached a high level. Therefore an enlargement of the design space by means of new or advanced aerodynamic methods is necessary in order to achieve further enhancements of performance and effici
Publikováno v:
International Journal of Turbomachinery, Propulsion and Power; Volume 2; Issue 1; Pages: 1
The following paper deals with the development of an optimized non-axisymmetric endwall contour for reducing the total pressure loss and for homogenizing the outflow of a highly-loaded compressor cascade. In contrast to former studies using a NACA-65