Journal ArticleDOI
Experimental and Numerical Study of Stall Flutter in a Transonic Low-Aspect Ratio Fan Blisk
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TLDR
In this article, high response flush mounted miniature pressure transducers are utilized to measure the aerodynamic loading distribution in the tip region of the fan for both subsonic/transonic and supersonic stall-side flutter regimes.Abstract:
Experiments are performed on a modern design transonic shroudless low-aspect ratio fan blisk that experienced both subsonic/transonic and supersonic stall-side flutter. High-response flush mounted miniature pressure transducers are utilized to measure the unsteady aerodynamic loading distribution in the tip region of the fan for both flutter regimes, with strain gages utilized to measure the vibratory response at incipient and deep flutter operating conditions. Numerical simulations are performed and compared with the benchmark data using an unsteady three-dimensional nonlinear viscous computational fluid dynamic (CFD) analysis, with the effects of tip clearance, vibration amplitude, and the number of time steps-per-cycle investigated. The benchmark data are used to guide the validation of the code and establish best practices that ensure accurate flutter predictions.Copyright © 2003 by ASMEread more
Citations
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Journal ArticleDOI
Nonsynchronous Vibration (NSV) due to a Flow-Induced Aerodynamic Instability in a Composite Fan Stator
TL;DR: In this article, the identification and prediction of a new class of non-synchronous vibration (NSV) problem encountered during the development of an advanced composite fan stator for an aircraft engine application is described.
Journal ArticleDOI
Tip Clearance Effects on Aero-elastic Stability of Axial Compressor Blades
Proceedings ArticleDOI
Aeromechanics Analysis of a Boundary Layer Ingesting Fan
TL;DR: In this paper, high-fidelity computational analysis of the fan a eromechanics is integral to the ongoing effort to design a boundary layer ingesting inlet and fan for fabrication and wind tunnel test.
Proceedings ArticleDOI
Numerical Study on Aeroelastic Instability for a Low-speed Fan
TL;DR: In this paper, the authors analyzed the flutter stability of a low speed/low pressure ratio fan blade in 1F (first flap) mode by using a validated CFD model (AU3D).
Journal ArticleDOI
Investigation of Flow Instability Mechanism Causing Compressor Rotor-Blade Nonsynchronous Vibration
Hongsik Im,Gecheng Zha +1 more
TL;DR: In this article, the aerodynamic excitation mechanism of the rotor-tip flow instabilities leading to nonsynchronous vibration in a high-speed multistage axial compressor was investigated using an unsteady Reynolds-averaged Navier-Stokes solver with a fully conservative, sliding interface.
References
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Journal ArticleDOI
The Role of Tip Clearance in High-Speed Fan Stall
TL;DR: In this article, a numerical experiment has been carried out to define the nearstall casing endwall flow field of a high-speed fan rotor, and the results of the simulation show that the interaction of the tip leakage vortex and the in-passage shock plays a major role in determining the fan flow range.
Journal ArticleDOI
Recommendations for Achieving Accurate Numerical Simulation of Tip Clearance Flows in Transonic Compressor Rotors
Dale E. Van Zante,Anthony J. Strazisar,Jerry R. Wood,Michael D. Hathaway,Theodore H. Okiishi +4 more
TL;DR: In this paper, the authors compare measured tip clearance flow details (e.g., trajectory and radial extent) with corresponding data obtained from a numerical simulation and make recommendations for achieving accurate numerical simulation of tip clearance flows.
Journal ArticleDOI
Calculation of Tip Clearance Effects in a Transonic Compressor Rotor
TL;DR: In this paper, the flow through the tip clearance region of a transonic compressor rotor (NASA rotor 37) was computed and compared to aerodynamic probe and laser anemometer data.
Journal Article
Mistuning Identification of Bladed Disks Using a Fundamental Mistuning Model-Part II: Application (2003-GT-38953)
J. H. Griffin,D. M. Feiner +1 more
TL;DR: In this paper, a reduced-order model of mistuning called the fundamental mistuning model (FMM) is used to identify bladed disks by measuring the vibratory response of the whole system.
Proceedings ArticleDOI
Mistuning Identification of Bladed Disks Using a Fundamental Mistuning Model: Part 2 — Application
D. M. Feiner,Jerry H. Griffin +1 more
TL;DR: In this article, the authors presented experimental validation of a new method of mistuning identification based on measurements of the vibratory response of the system as a whole, which is particularly suited to integrally bladed rotors, whose blades cannot be removed for individual measurements.
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