Results 221 to 230 of about 1,092 (255)
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Experimental investigation and design of a shape-variable compressor cascade
CEAS Aeronautical Journal, 2016The design of jet engine compressor blading always implies a compromise between design and off-design operation. The reason for this is a fixed blade geometry which has to be operated over a wide range of operating conditions. Consequently, maximum achievable efficiencies at design operation are limited by off-design requirements, e.g., a certain stall
Krone, Jan-Hendrik +6 more
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Design consideration for multi-lingual cascading text compressors
Proceedings DCC'99 Data Compression Conference (Cat. No. PR00096), 1999Summary form only given. We study the cascading of LZ variants to Huffman coding for multilingual documents. Two models are proposed: the static model and the adaptive (dynamic) model. The static model makes use of the dictionary generated by the LZW algorithm in Chinese dictionary-based Huffman compression to achieve better performance.
Chi, Chi-Hung, Zhang, Yan
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Separated Flow in a Straight Compressor Cascade
1991Experimental results are presented concerning separated incompressible flow through two linear compressor cascades at off-design conditions. The first cascade denoted as RK3 has already been tested at high positive and low negative incidence angles. The second cascade having NACA 65–1810 profile was measured at high positive incidence angle.
J. Citavý, M. Dušek
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Design and Optimization of Tandem Arranged Cascade in a Transonic Compressor
Journal of Thermal Science, 2017This study proposed a design and optimization strategy for a tandem arranged cascade using the Non-dominated Sorting Genetic Algorithm (NSGA) II multi-objective optimization algorithm and Back Propagation (BP) neural network technology. The NASA Stage 35 was employed as the initial bench mark in the present study and five geometric control parameters ...
Haitong Wang, Yangang Wang, Lai Wei
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On Aerodynamic Loading of Linear Compressor Cascades
Volume 1: Turbomachinery, 1992A study is presented concerning a high loading of the pressure surface of a blade in a linear compressor cascade. Assuming the two–dimensional incompressible flow, two cascades denoted as RK3 and VD17 have been designed using an inverse method developed previously at SVÚSS.
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Experimental Investigation on Droplet Behaviour in a Transonic Compressor Cascade
Volume 2A: Turbomachinery, 2014In recent years overspray fogging has become a powerful means for power augmentation of industrial gas turbines. Most of the studies concerning this topic focus on the problem from a thermodynamic point of view as summarized by Eisfeld and Joos [1]. Only a few studies, however, were undertaken to investigate the droplet behavior in the flow channel of ...
Niklas Neupert, Birger Ober, Franz Joos
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Studies of secondary flow at endwall of a supersonic compressor cascade
AIAA Journal, 1998A combined experimental and numerical study was conducted to investigate the endwall secondary flow in a linear supersonic compressor cascade. The experiment was carried out in a supersonic wind tunnel, with Mach and Reynolds numbers (based on the blade chord) of 2.36 and 4.8 X 106, respectively. A three-dimensional viscous computational fluid dynamics
Denver J. Osborne +2 more
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Modeling of Water Droplets Erosion on a Subsonic Compressor Cascade
Flow, Turbulence and Combustion, 2019In this paper an analysis of the erosion mechanism of water droplets impacting a compressor blade is performed. Three different models are compared: the Springer et al. model, developed in 1974 for predicting rain erosion on wind turbine blades; a new model developed by the authors to predict water droplet erosion on stainless steel surfaces and ...
Venturini P. +4 more
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Unsteady acoustic wave propagation in a transonic compressor cascade
34th Aerospace Sciences Meeting and Exhibit, 1996The need for improved performance and reduced noise levels has motivated engineers to assess the effects of flow unsteadiness on the aeroacoustic phenomena present in axial-flow turbomachines. A primary source of adverse aeroacoustic effects (noise) and performance degradation is the aerodynamic interaction between adjacent blade rows.
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