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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.
M. Eric Lyall +3 more
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Optimization of a Multistage Axial Compressor Stochastic Approach
Volume 1: Turbomachinery, 1992A procedure of a multistage axial compressor (MAC) parameters optimization in stochastic setting has been offered. The procedure allows to obtain a stable solution from the point of view of its practical realization. A concept of robustness (stability) of turbomachine optimum design has been introduced, and the criteria of stability degree evaluation ...
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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
S. G. Koff, E. M. Greitzer
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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
G. A. PLOURDE, A. H. STENNING
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Numerical Simulation of Particulates in Multi-Stage Axial Compressors
Volume 2A: Turbomachinery, 2016Aircraft engines ingest airborne particulate matter, such as sand, dirt, and volcanic ash, into their core. The ingested particulate is transported by the secondary flow circuits via compressor bleeds to the high pressure turbine and may deposit resulting in turbine fouling and loss of cooling effectiveness.
Swati Saxena +3 more
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Case wall pressures in a multistage axial compressor with tip clearance variation
Journal of Propulsion and Power, 1996Large cyclical pressure excursions from stator-averaged values are observed on the suction side of a rotor blade at the case wall in a multistage compressor as the rotor moves relative to the stator. The pressure changes correlate well with stator relative position, occur in the passage away from the blade, and are only slightly modified by tip ...
Moyle, I.N., Shreeve, R.P., Walker, G.J.
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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.
Wenhai Du +2 more
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An Analytical Method for the Fault Diagnosis of Axial Multistage Compressors
Volume 3: Coal, Biomass and Alternative Fuels; Combustion and Fuels; Oil and Gas Applications; Cycle Innovations, 1991A deterministic approach for troubleshooting in axial multistage flow compressors, that is to say, the solution of the diagnostic or inverse problem is presented. The approach utilizes a model which is capable of predicting the compressor performance with and without faults — solution of analysis or direct problems — previously developed
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Volume 1: Aircraft Engine; Marine; Turbomachinery; Microturbines and Small Turbomachinery, 2001
In this second part of a two-part paper on the application of the NASA multistage aerodynamic simulation CFD tool, the APNASA code, work is presented on how the code was used successfully in the design of a brand new, four-stage axial compressor aimed for a modern turbofan engine.
Y. Dong +3 more
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In this second part of a two-part paper on the application of the NASA multistage aerodynamic simulation CFD tool, the APNASA code, work is presented on how the code was used successfully in the design of a brand new, four-stage axial compressor aimed for a modern turbofan engine.
Y. Dong +3 more
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Investigation of mixing in a multistage axial compressor
1990Thesis (M.S.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1990. ; Includes bibliographical references (leaves [106]-[108]). ; by Sasi K. Digavalli. ; M.S.
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