Topic
Axial compressor
About: Axial compressor is a research topic. Over the lifetime, 12035 publications have been published within this topic receiving 127766 citations.
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TL;DR: In this article, the kink angles of diffuser inlet both at the hub and at the cylinder are fixed exclusively for the purpose of evening out the energy profile over the duct height at the last rotor blade row in order to shorten the diffuser system and to optimise it in part load operation.
Abstract: In an axial flow gas turbine with reaction blading, whose outlet rotor blades (14) are followed by a diffuser with axial outlet into an exhaust gas pipe (13), the kink angles of the diffuser inlet both at the hub (10) and at the cylinder (9) are fixed exclusively for the purpose of evening out the energy profile over the duct height at the outlet from the last rotor blade row in order to shorten the diffuser system and to optimise it in part load operation. In addition, a mechanism provided to remove swirl from the swirling flow in the form of profile ribs (17). Where the outlet rotor blades have a high Mach number flow, which leads to a large opening angle of the blading, the diffuser is subdivided into several partial diffusers (16) via sheet metal guides (15).
51 citations
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10 Dec 1997TL;DR: In this article, the effect of a time varying B-parameter on the post stall transients of an axial compressor is demonstrated through simulations of a compression system with speed control.
Abstract: The compressor stall/surge model of Moore and Greitzer (1986) is extended to include the spool dynamics. This results in a model with four states, where the new state is the B-parameter. The effect of a time varying B-parameter on the post stall transients of an axial compressor is demonstrated through simulations of a compression system with speed control.
51 citations
01 Jan 1980
TL;DR: In this article, a laser anomometer system employing an efficient data acquisition technique has been used to make measurements upstream, within, and downstream of the compressor rotor using fluorescent dye technique.
Abstract: A laser anomometer system employing an efficient data acquisition technique has been used to make measurements upstream, within, and downstream of the compressor rotor. A fluorescent dye technique allowed measurements within endwall boundary layers. Adjustable laser beam orientation minimized shadowed regions and enabled radial velocity measurements outside of the blade row. The flow phenomena investigated include flow variations from passage to passage, the rotor shock system, three-dimensional flows in the blade wake, and the development of the outer endwall boundary layer. Laser anemometer measurements are compared to a numerical solution of the streamfunction equations and to measurements made with conventional instrumentation.
51 citations
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TL;DR: In this paper, the 3D separations on the blade suction surface were largely removed by the tip clearance flow for clearance about 0.58% of chord, and the removal mechanism was associated with the suppression of the leading edge horseshoe vortex and the interaction of Tip clearance flow with the endwall boundary layer, which develops into a secondary flow as it is drifted towards the blade surface.
Abstract: This paper considers the interaction of tip clearance flow with three-dimensional (3D) separations in the corner region of a compressor cascade. Three-dimensional numerical computations were carried out using ten levels of tip clearance, ranging from zero to 2.18% of blade chord. The 3D separations on the blade suction surface were largely removed by the clearance flow for clearance about 0.58% of chord. For this cascade, experimental results at zero and 1.7% chord tip clearance were used to assess the validity of the numerical predictions. The removal mechanism was associated with the suppression of the leading edge horseshoe vortex and the interaction of tip clearance flow with the endwall boundary layer, which develops into a secondary flow as it is drifted towards the blade suction surface. Such interaction leads to the formation of a new 3D separation line on the endwall. The separation line forms the base of a separated stream surface which rolls up into the clearance vortex.Copyright © 2006 by ASME
51 citations
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TL;DR: In this article, a meanline design procedure for single-stage axial flow turbines is developed to find optimum turbine geometry and efficiency in a wide range of operating conditions, and the variation of the predicted turbine efficiency with loading coefficient, flow coefficient, specific speed and specific diameter is shown through new general maps.
51 citations