Results 21 to 30 of about 7,604 (310)
International Journal of Turbomachinery, Propulsion and Power, 2023 The tip gap region of an axial compressor rotor is a source of complex flows, inducing losses and stability issues. Recent works have proven the ability of blowing high-speed jets in the tip region to improve the surge margin of an axial compressor stage
Clémence Rannou +3 more
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AerospaceThe internal losses in the tip clearance region strongly influence the compressor performance and its operational range. Previous research proved that passive wall treatments with circumferential grooves in axial compressors effectively increase the ...
Ruben Bruno Diaz +4 more
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Test problem of flow modelling in the Rotor 37 compressor stage
Авіаційно-космічна техніка та технологія, 2023 The subject of the study is the dependence of the degree of pressure increase on the airflow in the impeller of the axial compressor degree. The object of study is the Rotor 37 axial compressor.
Andrii Duliepov +4 more
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The investigation of absolute flow non-uniform velocity distributions influence at the centrifugal compressor axial radial impeller inlet using numerical calculation methods in ANSYS CFX [PDF]
E3S Web of Conferences, 2019 Currently, methods of numerical modelling are widely used. They are especially widely used in the design of turbo compressors. For the specific task of designing new flowing parts of a centrifugal compressor, it is not recommended to deviate from the ...
Rakhmanina L.A. +4 more
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International Journal of Rotating Machinery, 2014 This paper presents experimental results of a single stage transonic axial flow compressor coupled with low porosity bend skewed casing treatment. The casing treatment has a plenum chamber above the bend slots.
Dilipkumar Bhanudasji Alone +6 more
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Quasi-2D Performance Analysis for Axial Compressors Based on Time-Marching Method
Xibei Gongye Daxue Xuebao, 2020 In order to get a fast performance analysis tool for multi-stage axial compressors, a quasi-two dimensional analysis model based on time-marching method is developed in this paper.
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Авіаційно-космічна техніка та технологіяThe operation of gas turbine engines inevitably increases the blade roughness and tip clearance in multistage axial compressors. The result is an increase in its thermogasodynamic parameters. The reason for the increase in the roughness of the blades and
Vadym Datsenko
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Method of aerodynamic improvement of axial and centrifugal compressor stages of gas turbine engines
Авіаційно-космічна техніка та технологіяThe development of approaches to aerodynamic improvement of compressor stages of gas turbine engines based on numerical modeling of three-dimensional turbulent gas flows remains a pressing task, which is of great importance for the design and ...
Natalya Zinevich
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Journal of Mechanical Engineering and Sciences, 2020 Splitter blades located between stator blades in a single-stage axial compressor were proposed and investigated in this work to find their effects on aerodynamic performance and operating stability.
K. Q. Pham, X. T. Le, C. T. Dinh
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