...Thomas Gianoli; Jean-François Boussuge; Pierre Sagaut; Jérôme de Laborderie This article presents the study of a subsonic inter-compressor S-duct. Numerical simulations are performed using large-eddy simulation (LES) based on a compressible hybrid thermal lattice Boltzmann method (LBM) implemented...

... by harmonic basis. This approximation allows studying the contribution to stall of each circumferential mode separately. The methodology has been assessed for the NASA rotor 67. The maximum amplitude of total pressure distortion at which the compressor becomes unstable and triggers a stall process has been...

...Pawel J. Przytarski; Andrew P. S. Wheeler In this paper, we study the effect of rotor-stator axial gap on midspan compressor loss using high-fidelity scale-resolving simulations. For this purpose, we mimic the multi-stage environment using a new numerical method that recycles wake unsteadiness from...

...Marcus Lejon; Niklas Andersson; Lars Ellbrant; Hans Mårtensson In this paper, the impact of manufacturing variations on performance of an axial compressor rotor is evaluated at design rotational speed. The geometric variations from the design intent obtained from measurements were used to evaluate...

...C. Aalburg; A. Simpson; M. B. Schmitz; V. Michelassi; S. Evangelisti; E. Belardini; V. Ballarini Two stators of a multistage centrifugal compressor with progressively smaller outer radii have been designed, built, and tested. The aim was to achieve a significant reduction in the outer diameter...

...Takanori Shibata; Manabu Yagi; Hideo Nishida; Hiromi Kobayashi; Masanori Tanaka The authors previously found that compressor stage efficiency in a high specific speed range was significantly improved by employing an increased relative velocity diffusion ratio coupled with a high backsweep angle...

...Hua Chen; Feng Shen; Xiao-Cheng Zhu; Zhao-Hui Du A three-dimensional compressible flow model is presented to study the occurrence of weak rotating waves in vaneless diffusers of centrifugal compressors. The diffuser considered has two parallel walls, and the undisturbed flow is assumed...

... aerial vehicles. These inlet systems can produce complex swirl patterns in addition to total pressure distortion. The effect of swirl distortion on engine or compressor performance and operability must be evaluated. The gas turbine community is developing methodologies to measure and characterize swirl...

...Y.-J. Chan; D. J. Ewins Integral bladed disks (also known as blisks) are more widely used in modern aeroengine compressor designs because of the potential weight savings, but there are challenges in controlling the extreme vibration response levels in mistuned blisks, which are blisks with blades...

...Liu He; Peng Shan Integrating a genetic algorithm code with a response surface methodology code based on the artificial neural network model, this paper develops an optimization system. By introducing a quasi-three-dimensional through-flow design code and a design code of axial compressor airfoils...

... is used to predict turbine and compressor end wall flows, flow around a fan blade section, jet flows, and a cutback trailing edge. Also, application of NLES to the flow in an idealized high pressure compressor drum cavity is considered. Generally, encouraging results are found. However, challenges remain...

... 02 2009 24 03 2009 30 06 2011 30 06 2011 aerospace engines compressors engines exhaust systems nozzles aerodynamics radial turbines unsteady flow turbocharger quasi-steady double entry The modern turbocharger remains one of the best means to achieve...

... the static pressure of tip-gap flow emerging from blade suction-side. Lastly, an approximate speed scaling developed for the DBD force helped estimate force requirements for stall margin enhancement of transonic rotors. Cumpsty , N. , 1989 , Compressor Aerodynamics , Krieger , Malabar, FL...

... for a high-speed compressor using a Coanda surface near the trailing edge in order to inhibit boundary layer separation. The design intent is to reduce the number of vanes while—in order to ensure a good matching with the downstream rotor—the flow turning angle is kept constant. In a first step, numerical...

... could be achieved, a decrease of the total pressure losses was possible for a few operating points only. Fottner , L. , 1979 , “ Theoretical and Experimental Investigations on Aerodynamically Highly-Loaded Compressor Bladings With Boundary Layer Control ,” Proceedings of the Fourth ISABE...

...Martin N. Goodhand; Robert J. Miller This paper considers the effect of small variations in leading edge geometry, leading edge roughness, leading edge fillet, and blade fillet geometry on the three-dimensional separations found in compressor blade rows. The detrimental effects of these separations...

...Arman Mohseni; Erik Goldhahn; René A. Van den Braembussche; Joerg R. Seume In centrifugal compressors, variable inlet guide vanes (IGVs) are used to control the mass flow rate with negligible change in pressure ratio and shaft speed. The efficient operation of IGVs is limited to the range...

...Tim Houghton; Ivor Day This paper concerns the optimization of casing grooves and the important influence of stall inception mechanism on groove performance. Installing casing grooves is a well known technique for improving the stable operating range of a compressor, but the wide-spread use...

... harmonic balance method is derived and adapted to phase lag periodic conditions to allow the simulation of only one blade passage per row regardless of row blade counts. Sophisticated space and time interpolations are involved and detailed. The test case is a single stage subsonic compressor. A convergence...

... temperature, and when the feedback wavelength matches within one or two blade pitches, the system becomes resonant and very high vibrations can occur on the blade. An axial stage compressor test rig is set-up to look into the underlying mechanism behind NSV through targeted measurements using both static...