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: Theoretical formulations for axial-flow impeller performance were evaluated based on a blade-element theory as discussed by the authors, which enable the calculation of the head and power vs. flow-rate curves of axial flow impellers.
Abstract: Theoretical formulations for impeller performance were evaluated based on a blade-element theory. These enable the calculation of the head and power vs. flow-rate curves of axial-flow impellers. The technique uses the lift and drag coefficients of the blade section of an impeller to calculate the spanwise swirl-velocity distribution. Using the angular-momentum equation, it is possible to calculate the corresponding spanwise distribution of the energy head of the impeller. Integration of these distributions of head and torque gives the impeller's performance. Parameters including the flow number, the power number, the thrust force number, and the swirl velocity can be found at the impeller operating point, determined using the head curve and an experimentally calibrated resistance curve. A laser Doppler velocimetry (LDV) system was used to measure the velocity distribution for different axial flow impellers in mixing tanks. Calculated flow and power numbers agreed well with the experimental results. Using the blade's spanwise head distribution and a set of calibrated flow-resistance data, it is also possible to estimate an impeller's outlet axial-velocity distribution. Predictions compared well with LDV experimental data. The effect of impeller-blade angle, number of blades, blade camber, and blade thickness on the performance of axial-flow impellers was investigated using the Agitator software.
36 citations
TL;DR: In this article, an apparatus designed to subject a liquid column or bridge to an axial flow is described, where the bridge liquid is density matched to the water in the external flow in order to simulate low gravity (∼10 -3 Earth g).
36 citations
TL;DR: In this paper, a highly loaded low-pressure turbine blade in a low-speed linear cascade facility was used to demonstrate the role of boundary layer transition in this separated region, and higher-order turbulence statistics were used to identify transition and separation zones.
Abstract: Flow measurements were made on a highly loaded low pressure turbine blade in a low-speed linear cascade facility. The blade has a design Zweifel coefficient of 1.34 with a peak pressure coefficient near 47% axial chord (mid-loaded). Flow and surface pressure data were taken for Rec = 20,000 with 3% inlet freestream turbulence. For these operating conditions, a large separation bubble forms over the downstream portion of the blade suction surface, extending from 59% to 86% axial chord. A Single-element hotfilm measurements were acquired to clearly identify the role of boundary layer transition in this separated region. Higher-order turbulence statistics were used to identify transition and separation zones. Similar measurements were also made in the presence of unsteady forcing using pulsed vortex generator jets just upstream of the separation bubble (50% cx ). Measurements provide a comprehensive picture of the interaction of boundary layer transition and separation in this unsteady environment. Similarities between pulsed flow control and unsteady wake motion are highlighted.Copyright © 2006 by ASME
36 citations
TL;DR: In this paper, the authors trace the origins of the GE Design System and how it has evolved from early methods to underlie and supplement present CFD methods, which are not themselves discussed herein.
Abstract: This paper traces the origins of the GE Design System and how it has evolved from early methods to underlie and supplement present CFD methods, which are not themselves discussed herein. The two main elements of the detailed aero design process are vector diagram establishment and airfoil design. Their evolution is examined, and examples of how they were used to design some early GE compressors of interest are given. By the late 1950s, some transonic airfoil shapes were being custom tailored using internal blade station data from more complete radial equilibrium solutions. In the 1960s, rules for shaping transonic passages were established, and by the 1970s, custom tailoring was done for subsonic blading as well. The preliminary design layout process for a new compressor is described. It involves selecting an annulus shape and blading overall proportions that will allow a successful detailed design to follow. This requires establishment of stage loading limits that permit stall-free operation, and an efficiency potential prediction method for state-of-the-art blading. As design methods evolved, the newer approaches were calibrated with data-match experience, a process that is expected to always be needed.
36 citations
Patent•
09 Jan 1991
TL;DR: In this article, a combination of a variable reluctance motor and a screw compressor is provided with a fluid management system that directs a portion of the lubricant flow through the VL motor to cool its stator laminations and windings.
Abstract: A combination of a variable reluctance motor and a screw compressor is provided with a fluid management system that directs a portion of the lubricant flow through the variable reluctance motor to cool its stator laminations and windings Another portion of the lubricant flow is caused to pass directly from a heat exchanger to the screw compressor The first portion of flow, which passes through the variable reluctance motor, is then directed into fluid communication with the inlet of the screw compressor to lubricate the screw compressor and provide cooling for the compressor The portion of lubricant flow passing directly through the heat exchanger to the compressor also provides lubrication for the compressor and is used to further cool the moving parts of the screw compressor
36 citations