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AIAA Journal, 1980
Introduction B the term transonic compressor we mean an axial flow compressor in which the inlet flow Mach number, relative to the rotating blades, varies from below unity at radii near the inner casing or hub to values substantially above unity at radii near the blade tips.
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Introduction B the term transonic compressor we mean an axial flow compressor in which the inlet flow Mach number, relative to the rotating blades, varies from below unity at radii near the inner casing or hub to values substantially above unity at radii near the blade tips.
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Optimization of Robust Transonic Compressor Blades
Volume 2C: Turbomachinery, 2016Surface degradation in an axial compressor during its lifetime can have a considerable adverse effect on its performance. The present study investigates how the optimized design of compressor blades in a single compressor stage is affected by considering a high level of surface roughness on a level representative of a long period of in-service use.
Marcus Lejon +4 more
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Design of Aerodynamically Balanced Transonic Compressor Rotors
Journal of Turbomachinery, 2023Abstract This paper describes a simple and efficient physics-based method for designing optimal transonic multistage compressor rotors. The key to this novel method is that the spanwise variation of the parameter which controls the three-dimensional shock structure, the area ratio between the throat and the inlet, “Athroat /Ainlet”, is ...
Demetrios Lefas, Robert J. Miller
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Aerodynamics of swept and leaned transonic compressor-rotors
Applied Energy, 2007Abstract A systematic investigation to understand the impact of axially swept and tangentially leaned blades on the aerodynamic behaviour of transonic axial-flow compressor rotors was undertaken. Effects of axial and tangential blade curvature were analyzed separately.
BENINI, ERNESTO, BIOLLO, ROBERTO
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Time Transformation Simulation of 1.5 Stage Transonic Compressor
Volume 2C: Turbomachinery, 2015The accurate prediction of the aerodynamic and aeromechanical performance in a modern transonic compressor often exceeds the capability of traditional steady state mixing plane simulation methods. Time accurate transient blade row simulation approaches are required when there is a close coupling of the flow between the blade rows, and for fundamentally
Laith Zori +3 more
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Tip-Vortices in Transonic Axial-Compressors
2002A great potential regarding powerfull loss reduction in transonic axial flow compressors is located at the blades’ tip. In this region losses are intensified by tip-vortices standing above the suction sides of the blades. Each vortex propagates through the blade duct in question and must cross the passage shock which is caused by the flow deflection on
Willy Hofmann, Josef Ballmann
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Aerodynamics of a Transonic Centrifugal Compressor Impeller
Volume 5: Turbo Expo 2002, Parts A and B, 2002High pressure ratio centrifugal compressors are applied to turbochargers and turboshaft engines because of their small dimensions, high efficiency and wide operating range. Such a high pressure ratio centrifugal compressor has a transonic inlet condition accompanied with a shock wave in the inducer portion.
Seiichi Ibaraki +4 more
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Multiple tone generation by transonic compressors
Journal of Sound and Vibration, 1971Abstract An axial flow compressor operating at relative tip speeds in excess of the speed of sound generates a multiple tone acoustic field. A theory is presented which explains this tone field in terms of the production and propagation of the shock waves associated with the supersonic elements of the blading.
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Flow in Multistage Transonic Compressors
2019The project has been funded by the Engineering and Physical Sciences Research Council (EPSRC) and Siemens Industrial Turbomachinery Ltd.
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Aeroelastic Investigation of a Transonic Research Compressor
Volume 7B: Structures and Dynamics, 2013The trend in modern compressor design is towards higher stage loading and less structural damping, resulting in increased flutter risk. The understanding of the underlying aeroelastic effects, especially at highly loaded BLISK rotors, is small. This paper reports on the analysis of flutter phenomena in a modern transonic compressor.
S. Leichtfuß +4 more
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