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Filippo Merli, Nicolas Krajnc, Asim Hafizovic, Marios Patinios and Emil Göttlich
The purpose of the paper is to characterize the aerodynamic behavior of a rotor-downstream hub cavity rim seal in a high-pressure turbine (HPT) stage. The experimental data are acquired in the Transonic Test Turbine Facility at the Graz University of Tec...
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Hengtao Shi and Xianjun Yu
This paper proposes a stage flow parameter analytical model for rapid evaluation of a counter-rotating compressor?s performance for design optimization and its application in the design of a transonic counter-rotating fan. In the first part, the velocity...
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Xiaojun Yang, Hongming Cai, Jinhui Kang, Wenbo Liu and Peiran Li
In modern civil aeroengines, the hot streak and swirl at the exit of the combustor have a significant impact on the aerothermal performance of the high-pressure turbine (HPT). Due to the different design purposes of the combustor and the turbine, hot str...
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Yun Zheng, Xiubo Jin and Hui Yang
Asymmetric vane pitch is a key technique to suppress the forced response of downstream rotor blades. To address the problem of low-engine-order (LEO) excitation with high amplitude under an asymmetric configuration (half-and-half layout) widely recognize...
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Pawel Flaszynski, Michal Piotrowicz and Tommaso Bacci
Investigations of combustors and turbines separately have been carried out for years by research institutes and aircraft engine companies, but there are still many questions about the interaction effect. In this paper, a prediction of a turbine stator?s ...
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Stéphane Moreau
In future Ultra-High By-Pass Ratio turboengines, the turbomachinery noise (fan and turbine stages mainly) is expected to increase significantly. A review of analytical models and numerical methods to yield both tonal and broadband contributions of such n...
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Wei Huang, Kailin Yang, Xinlei Guo, Jiming Ma, Jue Wang and Jiazhen Li
Complete characteristic curves of a pump-turbine are essential for simulating the hydraulic transients and designing pumped storage power plants but are often unavailable in the preliminary design stage. To solve this issue, a prediction method for the c...
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Giovanna Barigozzi, Silvia Mosconi, Antonio Perdichizzi and Silvia Ravelli
Hot streak migration in a linear vane cascade with showerhead film cooling was experimentally and numerically investigated at isentropic exit Mach number of Ma2is = 0.40, with an inlet turbulence intensity level of Tu1 = 9%. Two tangential positions of t...
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Axel Holewa, Sergey Lesnik, Graham Ashcroft and Sébastien Guérin
The interaction of steady hot streaks from an annular ring of combustion chambers with turbine rotating blades can potentially generate tonal noise. The relevance of this source mechanism in aeroengine noise is controversially discussed in the literature...
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D. G. Knost and K. A. Thole
Pág. 297 - 305
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