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Axial compressor

About: Axial compressor is a research topic. Over the lifetime, 12035 publications have been published within this topic receiving 127766 citations.


Papers
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Journal ArticleDOI
TL;DR: In this paper, a series of configurations of casing treatment were compared to obtain the optimum ones judged from above-mentioned two standpoints: larger stall margin improvement and smaller lowering of efficiency.
Abstract: Casing treatment is known to improve the stall margin of axial compressors. However, it is known as well that casing treatment lowers the efficiency of compressors. An experiment was planned in order to test a series of configurations of casing treatment which are supposed to have favourable effects and to obtain the optimum ones, if any, judged from above-mentioned two standpoints: larger stall margin improvement and smaller lowering of efficiency. The result shows that the relation between the stall margin imp improvement and the compressor efficiency for all of the tested configurations falls on some smooth curved-line, and thus, there exists no particularly superior treatment configuration to others. It rather shows that a certain amount of loss in efficiency is inevitable in order to obtain the required amount of stall margin improvement. Influence of rotor tip clearance on the effect of casing treatment was also examined. The result can be used as a guide for the selection of configurations in designing the casing treatment.

118 citations

Journal ArticleDOI
TL;DR: In this paper, an approximate method is presented with which both of these effects can be included in design through-flow calculations in axial-flow turbomachines, where substantial spanwise mixing of flow properties often occurs.
Abstract: Flow measurements taken in multistage axial-flow turbomachines suggest that substantial spanwise mixing of flow properties often occurs. In addition, measured blade row turnings often show considerable deviation from two-dimensional cascade theory, particularly in the end-wall regions. An approximate method is presented with which both of these effects can be included in design through-flow calculations. 21 refs.

117 citations

Patent
24 May 1991
TL;DR: A brushless DC motor has a rotor (10) with impeller blades (50) mounted thereon to pump blood through the central portion of the motor as mentioned in this paper, and the rotor has a cylindrical surface (20) that is spaced from a cooperating cylinrical surface on the motor stator.
Abstract: A brushless DC motor has a rotor (10) with impeller blades (50) mounted thereon to pump blood through the central portion of the motor. Over a portion of its length, the rotor (10) has a cylindrical surface (20) that is spaced from a cooperating cylindrical surface on the motor stator. There is a gap between these cylindrical surfaces through which there is a leakage flow of blood. The relative motion between the cylindrical surfaces provides a hydrodynamic bearing that suspends the rotor in the stator.

117 citations

Journal ArticleDOI
TL;DR: In this article, the axial, tangential, and radial components of relative velocity, as well as the static and stagnation pressures, were obtained at two axial locations, one at the rotor trailing edge, the other downstream of the rotor.
Abstract: Detailed measurements of the flow field in the tip region of an axial flow compressor rotor were carried out using a rotating five-hole probe. The axial, tangential, and radial components of relative velocity, as well as the static and stagnation pressures, were obtained at two axial locations, one at the rotor trailing edge, the other downstream of the rotor. The measurements were taken up to about 26 percent of the blade span from the blade tip. The data are interpreted to understand the complex nature of the flow in the tip region, which involves the interaction of the tip leakage flow, the annulus wall boundary layer and the blade wake. The experimental data show that the leakage jet does not roll up into a vortex. The leakage jet exiting from the tip gap is of high velocity and mixes quickly with the mainstream, producing intense shearing and flow separation. There are substantial differences in the structure of tip clearance observed in cascades and rotors.

115 citations

Journal ArticleDOI
TL;DR: In this article, a relatively simple model is used to examine the influence of various distortions in setting this instability point, and it is found that the model reproduces known experimental trends for the loss of stability margin with increasing distortion amplitude and with changes in reduced frequency.
Abstract: This paper describes the development of a new analysis to predict the onset of flow instability for an axial compressor operating in a circumferentialy distorted inlet flow. A relatively simple model is used to examine the influence of various distortions in setting this instability point. It is found that the model reproduces known experimental trends for the loss of stability margin with increasing distortion amplitude and with changes in reduced frequency. In particular, there is a recognizable 'critical sector angle' which characterizes loss of stability margin. To the authors' knowledge, this is the first time the effects described herein have been theoretically demonstrated as the direct result of a fluid dynamic stability.

114 citations


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Performance
Metrics
No. of papers in the topic in previous years
YearPapers
202398
2022304
2021217
2020288
2019316
2018353