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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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Proceedings ArticleDOI
13 Jun 1994
TL;DR: In this article, the role of the passage shock/vortex interaction in generating endwall blockage is discussed, and the radial influence of the tip clearance flow extends to 20 times the physical tip clearance height.
Abstract: Experimental and computational techniques are used to investigate tip clearance flows in a transonic axial compressor rotor at design and part speed conditions. Laser anemometer data acquired in the endwall region are presented for operating conditions near peak efficiency and near stall at 100% design speed and at near peak efficiency at 60% design speed. The role of the passage shock / leakage vortex interaction in generating endwall blockage is discussed. As a result of the shock / vortex interaction at design speed, the radial influence of the tip clearance flow extends to 20 times the physical tip clearance height. At part speed, in the absence of the shock, the radial extent is only 5 times the tip clearance height. Both measurements and analysis indicate that under part-speed operating conditions a second vortex, which does not originate from the tip leakage flow, forms in the endwall region within the blade passage and exits the passage near midpitch. Mixing of the leakage vortex with the primary flow downstream of the rotor at both design and part speed conditions is also discussed.Copyright © 1994 by ASME

60 citations

Journal ArticleDOI
TL;DR: In this article, a complete review of the most recent advances in the field of aerodynamic design and operation of transonic axial flow compressors is given, highlighting the most relevant contribution in this field and to suggest the prospects for future developments.

60 citations

Patent
29 Jun 1993
TL;DR: In this article, an axial flow turbomachine is provided having a diffuser that directs the flow of working fluid from a turbine exit to an exhaust housing having a bottom opening, thereby turning the flow 90° from the axial to radial direction.
Abstract: An exhaust system for an axial flow turbomachine is provided having a diffuser that directs the flow of working fluid from a turbine exit to an exhaust housing having a bottom opening, thereby turning the flow 90° from the axial to radial direction In the exhaust housing, the flow exiting at the top of the diffuser turns 180° from the vertically upward direction to the downward direction The strength of the vortex formed in the exhaust housing as a result of this turning is minimized by orienting the outlet of an outer exhaust flow guide portion of the diffuser so that it lies in a plane that makes an angle with a plane perpendicular to the turbine axis As a result, the minimum axial length of the outer flow guide occurs at a location remote from the exhaust housing outlet and the maximum axial length occurs at a location proximate the opening, thereby crowding the vortex against a radially extending baffle in the exhaust housing

60 citations

Patent
12 May 1993
TL;DR: In this article, a method and system for increasing the pressure of gaseous fuel delivered to a fuel system of a gas turbine engine is described, where a portion of pressurized gas or compressed air is discharged from a high-pressure section of the gas turbine and is communicated to a plurality of radial inflow turbines or axial flow turbines.
Abstract: A method and system for increasing the pressure of gaseous fuel delivered to a fuel system of a gas turbine engine. A portion of pressurized gas or compressed air is discharged from a high-pressure section of the gas turbine engine and is communicated to a plurality of radial inflow turbines or axial flow turbines. Energy is transferred from each turbine to a plurality of compressors driven by the turbines. Gaseous fuel is supplied to an inlet of one of the compressors. The compressed gaseous fuel is then cooled downstream of the compressors. The aftercooled and compressed gaseous fuel is delivered to the fuel system of the gas turbine engine.

60 citations

Patent
24 Jul 1952

60 citations


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