Results 211 to 220 of about 55,419 (236)
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Non-Uniform Tip Clearance Effects on Turbocharger Compressor Performance
Volume 2B: Turbomachinery, 2018In most turbocharger compressors, diffusers a re designed with contractions along the passage mainly for delaying surge. The width ratio parameter, B, which defines the diffuser inlet width to diameter ratio significantly affects the losses in the diffuser. Changes to tip clearance, for example, due to the impeller rubbing the shroud casing changes the
Richard A. Adjei +4 more
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Nonuniform Flow in a Compressor Due to Asymmetric Tip Clearance
Journal of Turbomachinery, 2000This paper presents an analytical study of flow redistribution in a compressor stage due to asymmetric tip clearance distribution. The entire stage is modeled as an actuator disk and it is assumed that upstream and downstream flow fields are determined by the local tip clearance. The flow is assumed to be inviscid and incompressible.
Seung Jin Song, Seung Ho Cho
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Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy, 2014
Tip injection has shown potential for controlling turbine tip clearance flows; however, the effects of tip injection may behave differently at design and off-design incidences. This paper computationally investigates the sensitivity of endwall flowfields and aerodynamics to flow incidence for flat and cavity tips at different injection locations, in ...
Jie Gao +3 more
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Tip injection has shown potential for controlling turbine tip clearance flows; however, the effects of tip injection may behave differently at design and off-design incidences. This paper computationally investigates the sensitivity of endwall flowfields and aerodynamics to flow incidence for flat and cavity tips at different injection locations, in ...
Jie Gao +3 more
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Journal of Visualization, 2020
In order to better understand the flow characteristics of mixed-flow pump with non-uniform tip clearance, a test rig is established and the flow fields of various cross section in impeller are studied based on particle image velocimetry technology. The velocity vector distributions of three cross sections, e.g., impeller blade inlet, middle and outlet,
Wei Li +4 more
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In order to better understand the flow characteristics of mixed-flow pump with non-uniform tip clearance, a test rig is established and the flow fields of various cross section in impeller are studied based on particle image velocimetry technology. The velocity vector distributions of three cross sections, e.g., impeller blade inlet, middle and outlet,
Wei Li +4 more
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Journal of Thermal Science, 2008
This paper presents a numerical investigation of effects of axial non-uniform tip clearances on the aerodynamic performance of a transonic axial compressor rotor (NASA Rotor 37). The three-dimensional steady flow field within the rotor passage was simulated with the datum tip clearance of 0.356 mm at the design wheel speed of 17188.7 rpm.
Hongwei Ma, Baihe Li
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This paper presents a numerical investigation of effects of axial non-uniform tip clearances on the aerodynamic performance of a transonic axial compressor rotor (NASA Rotor 37). The three-dimensional steady flow field within the rotor passage was simulated with the datum tip clearance of 0.356 mm at the design wheel speed of 17188.7 rpm.
Hongwei Ma, Baihe Li
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Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 2022
In this paper, the single-stage compressor with circumferential non-uniform tip clearance is experimentally investigated under 180° total pressure distortion for the compressor characteristics and the dynamic stall process. In the special structure of the circumferential non-uniform tip clearance, different circumferential distortion areas are adopted
Haoyang Xu, Jun Hu
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In this paper, the single-stage compressor with circumferential non-uniform tip clearance is experimentally investigated under 180° total pressure distortion for the compressor characteristics and the dynamic stall process. In the special structure of the circumferential non-uniform tip clearance, different circumferential distortion areas are adopted
Haoyang Xu, Jun Hu
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Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy, 2011
Tip leakage flow is responsible for a significant amount of aerodynamic losses in a turbine stage, and the mixing of leakage flow with the rotor passage secondary flow causes losses and reduces turbine stage efficiency. This article presents a numerical investigation of the effect of axially non-uniform tip clearance on the aerodynamic performance of ...
Jie Gao +3 more
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Tip leakage flow is responsible for a significant amount of aerodynamic losses in a turbine stage, and the mixing of leakage flow with the rotor passage secondary flow causes losses and reduces turbine stage efficiency. This article presents a numerical investigation of the effect of axially non-uniform tip clearance on the aerodynamic performance of ...
Jie Gao +3 more
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Volume 7: Fluids Engineering, 2016
In the unshrouded axial turbine, the tip clearances can result in the loss of turbine efficiency and the penalty of turbine performance. Therefore, investigating the blade tip geometry of improving the turbine performance has a great significance. This paper is to study the effects of non-uniform tip clearance on the flow field in a turbine cascade ...
Hongwei Ma, Yangtao Tian
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In the unshrouded axial turbine, the tip clearances can result in the loss of turbine efficiency and the penalty of turbine performance. Therefore, investigating the blade tip geometry of improving the turbine performance has a great significance. This paper is to study the effects of non-uniform tip clearance on the flow field in a turbine cascade ...
Hongwei Ma, Yangtao Tian
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Volume 6: Turbomachinery, Parts A, B, and C, 2008
The performance, efficiency, and stall inception of an axial compressor was investigated experimentally with small levels of rotor centerline offset. The measurements were acquired using a high-speed, single-stage compressor. The rotor was levitated magnetically during operation which allowed precise positioning of the rotor centerline within the ...
Scott C. Morris +4 more
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The performance, efficiency, and stall inception of an axial compressor was investigated experimentally with small levels of rotor centerline offset. The measurements were acquired using a high-speed, single-stage compressor. The rotor was levitated magnetically during operation which allowed precise positioning of the rotor centerline within the ...
Scott C. Morris +4 more
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Applied Ocean Research, 2011
The performance of a Wells turbine with various non-uniform tip clearances was investigated using computational fluid dynamics (CFD). The investigation was performed on numerical models of a NACA0020 blade profile under steady flow conditions. The performance of turbines with uniform and non-uniform tip clearances was compared.
Zahari Taha +3 more
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The performance of a Wells turbine with various non-uniform tip clearances was investigated using computational fluid dynamics (CFD). The investigation was performed on numerical models of a NACA0020 blade profile under steady flow conditions. The performance of turbines with uniform and non-uniform tip clearances was compared.
Zahari Taha +3 more
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