... aerodynamic design Compressor Self-excited aeroelastic stability, or flutter, of fan blades can limit the operating range of aero-engines. This restriction is expected to become more severe in the future as the need to reduce specific fuel consumptions calls for lighter, higher loaded blades...

.... , Bouldin , B. , and Krishnan , P. M. , 2011 , “ Compressor Performance and Operability in Swirl Distortion ,” ASME J. Turbomach. , 134 ( 4 ), p. 041008 . 10.1115/1.4003657 [4] Pardo , A. C. , Mehdi , A. , Pachidis , V. , and MacManus , D. G. , 2014 , “ Numerical Study...

... structure becomes asymmetric and hence requires a whole assembly numerical model. The type of asymmetry which appears at lower flow coefficients is similar to the multicell, part span rotating stall, which can occur on the front stages of core compressors at stable operating conditions. The numerical...

...Alexander Hehn; Moritz Mosdzien; Daniel Grates; Peter Jeschke A transonic centrifugal compressor was aerodynamically optimized by means of a numerical optimization process. The objectives were to increase the isentropic efficiency and to reduce the acoustic signature by decreasing the amplitude...

...Xinqian Zheng; Zhenzhong Sun; Tomoki Kawakubo; Hideaki Tamaki The nonuniformity of the flow field induced by a nonaxisymmetric volute significantly degrades the stability of a turbocharger centrifugal compressor. In this paper, a nonaxisymmetric vaned diffuser is investigated as a nonaxisymmetric...

... 20 10 2017 Boundary layer development Computational fluid dynamics Fan Fluid dynamics Turbine aerodynamic design Compressor Turbine components Gas turbine engines Heat transfer phenomena The quest for higher efficiency in modern gas-turbine engines is driving compressor...

...Feng Wang; Mauro Carnevale; Luca di Mare; Simon Gallimore Computational fluid dynamics (CFD) has been widely used for compressor design, yet the prediction of performance and stage matching for multistage, high-speed machines remains challenging. This paper presents the authors' effort to improve...

... centrifugal compressors. The factors influencing the presence and extent of this recirculation are numerous, requiring detailed investigations to successfully understand its sources and to characterize its extent. A combination of validated three-dimensional computational fluid dynamics (CFD) data and gas...

... Computational fluid dynamics Fan Turbine aerodynamic design Compressor BL = boundary layer c xIV = axial chord of IV CV/IV = conventional vane/integrated vane IV-3d = profiled integrated vane LE/TE = leading edge/trailing edge ML = mixing length NGV...

...Matthias Rolfes; Martin Lange; Konrad Vogeler; Ronald Mailach The demand of increasing pressure ratios for modern high pressure compressors leads to decreasing blade heights in the last stages. As tip clearances (TC) cannot be reduced to any amount and minimum values might be necessary for safety...

... Compressor Leaking flows In gas turbines, tip clearance exists between the turbine blade tips and casing wall in order to prevent rubbing. The hot gas is driven across this tip clearance due to the pressure difference between the blade pressure side and suction side. After the tip leakage flow...

... Computational fluid dynamics Fan Measurement techniques Turbomachinery blading Turbine aerodynamic design Compressor Design Researchers continue to develop technology to improve the efficiency of modern jet engines further. Much of the focus has been on the reduction of weight and the aerodynamic...

... blading Turbine aerodynamic design Compressor Design The trend to more aggressive aerodynamic blade design for higher efficiencies and mass flows is one demand the designer is confronted with during the design of next generation turbomachinery. In the case of large power generation gas...

...Alistair John; Shahrokh Shahpar; Ning Qin This paper describes the use of the free-form-deformation (FFD) parameterization method to create a novel blade shape for a highly loaded, transonic axial compressor. The novel geometry makes use of precompression (via an S-shaping of the blade around...

... measurement data and a NACA6510 compressor cascade. The predictions of the experimental values are in very good agreement with the experimental data, showing the capability of the model for designing riblet structured turbomachinery blading. 1 Corresponding author. Contributed by the International...

.... 27 09 2016 29 11 2016 Aeromechanical instabilities Computational fluid dynamics Fan Turbine aerodynamic design Compressor In recent years, civil turbofan engine designs have moved toward low specific thrust cycles in order to improve specific fuel consumption. This requires...

...Chunill Hah Effects of a large rotor tip gap on the performance of a one and a half stage axial compressor are investigated in detail with a numerical simulation based on large eddy simulation (LES) and available particle image velocimetry (PIV) data. This paper studies the main flow physics...

...Kiran Auchoybur; Robert J. Miller The operating range of a compressor is usually limited by the rapid growth of three-dimensional (3D) separations in the endwall flow region. In contrast, the freestream region is not usually close to its diffusion limit and has little effect on overall range...

...Aniwat Tiralap; Choon S. Tan; Eric Donahoo; Matthew Montgomery; Christian Cornelius Changes in loss generation associated with altering rotor tip blade loading of an embedded rotor–stator compressor stage are assessed with unsteady three-dimensional computations, complemented by control volume...

... diffuser experiments in a compressor stage and in a rotating swirling flow test rig. This is combined with steady and unsteady Reynolds-averaged Navier–Stokes (RANS) computations. The test article is a pressure ratio 5 turbocharger compressor with an airfoil vaned diffuser. The swirling flow rig is able...