Results 231 to 240 of about 18,174 (265)
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Axisymmetrically Stalled Flow Performance for Multistage Axial Compressors
Journal of Turbomachinery, 1986A study of the stalled flow performance of multistage axial compressors is presented. A proposal is made regarding the form of axisymmetric pumping performance in stall (which is a requisite of current rotating stall models) over the entire compressor flow range, including reversed flow. It is also shown that the axisymmetric performance can rise above
Edward M. Greitzer, S. G. Koff
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A Methodology for Variable Geometry Optimization of Multistage Axial Compressors
Volume 2A: Turbomachinery, 2017This paper presents a procedure for experimentally optimizing a multistage axial compressor. Due to the usual proprietary nature of such tests, a mean-line model of a nine-stage compressor with three rows of variable geometry is used instead of a real machine as a testbed for explaining the optimization method.
Douglas C. Rabe +3 more
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Optimization Method of the Multistage Axial Compressors Using CFD Simulation
International Journal of Computational Methods, 2021The current level of numerical methods of gas dynamics makes it possible to optimize compressors using 3D CFD models. However, the methods and means are not sufficiently developed for their wide application. This paper describes a new method for the optimization of multistage axial compressors based on 3D CFD modeling and summarizes the experience of ...
Grigorii Popov +5 more
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Turbomachinery, 2018
An axial compressor loss and deviation model that was developed and presented during previous research has now been used to develop a computer program for multistage compressor design.
M. Banjac, M. Petrovic
semanticscholar +1 more source
An axial compressor loss and deviation model that was developed and presented during previous research has now been used to develop a computer program for multistage compressor design.
M. Banjac, M. Petrovic
semanticscholar +1 more source
Turbomachinery, 2018
Part I of this paper presents a method and a computer program for the mean design of multistage axial compressors. This second part describes a method and an additional computer routine that use the basic mean line design to create a fully two ...
M. Banjac, M. Petrovic
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Part I of this paper presents a method and a computer program for the mean design of multistage axial compressors. This second part describes a method and an additional computer routine that use the basic mean line design to create a fully two ...
M. Banjac, M. Petrovic
semanticscholar +1 more source
Turbomachinery, 2018
Solid particle ingestion is one of the principal degradation mechanisms in the compressor and turbine sections of gas turbines. In particular, in industrial applications, the micro-particles not captured by the air filtration system can cause deposits on
Nicola Aldi +6 more
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Solid particle ingestion is one of the principal degradation mechanisms in the compressor and turbine sections of gas turbines. In particular, in industrial applications, the micro-particles not captured by the air filtration system can cause deposits on
Nicola Aldi +6 more
semanticscholar +1 more source
Study of the acoustic resonance occurring in a multistage high-speed axial compressor
Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy, 2013A study of the acoustic resonance occurring and leading to surge in the 3½-stage high-speed compressor CREATE (rotation speed: 11543 r/min, rotor 1 tip speed: 313 m/s) is presented in this paper. It is based on high-frequency wall static pressure measurements performed all along the machine from peak efficiency to surge.
Courtiade, Nicolas, Ottavy, Xavier
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Influence of Tip Clearance on the Performance and Matching of Multistage Axial Compressors
Volume 2A: Turbomachinery, 2016Tip clearance has great influence on the performance of multistage axial compressors including efficiency, pressure rise, mass flow, as well as matching. This paper reports a study into the influence of tip clearance on the performance and matching of a 5-stage axial compressor by a numerical method.
Xinqian Zheng, Heli Yang
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Attenuation of circumferential inlet distortion in multistage axial compressors.
Journal of Aircraft, 1968Circumferential inlet distortion in a high hub-tip ratio multistage machine is treated by analyzing the compressor as a region in which a large number of small stages produce a pressure rise that is a function of the local mass flow rate. The resistance to circumferential flow due to the blading is included through an empirical factor. It is found that
A. H. Stenning, G. A. Plourde
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Dynamic simulations of post-stall performance in multistage axial compressors
Journal of Thermal Science, 2012In this contribution a quasi-one-dimensional tool for stationary and transient simulations of post-stall flows in multistage axial compressors is presented. An adapted version of the 1D Euler equations with additional source terms is discretized with a finite volume method and solved in time by a fourth-order Runge-Kutta scheme.
JunQiang Zhu +2 more
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