7/22/2023 0 Comments Best turbo flutterSelf-excited blade vibration experimentally investigated in transonic compressors: rotating instabilities and flutter. Holzinger, F, Wartzek, F, Jüngst, M, Schiffer, H-P, Leichtfuss, S. A numerical study of flutter in a transonic fan. A review of aeroelasticity methods with emphasis on turbomachinery applications. Saravanamuttoo, HIH, Rogers, GFC, Cohen, H. France: Advisory Group for Aerospace Research and Development 1987. AGARD manual on aeroelasticity in axial-flow turbomachines. ![]() Development of instrumentation to capture unsteady & flutter phenomena in the fan rotors of gas turbine engines 2011:1–8 pp. Jha, BK, Rao, ANV, Pratap, A, Mohana, TR, Singh, AK, Khorikov, AA. A method and system for monitoring rotor blades of a turbomachine using blade tip timing (BTT) 2018. Proceedings of the National Aerospace Propulsion Conference. In: Mistry, C, Kumar, S, Raghunandan, B, Sivaramakrishna, G, editors. Rotor blade vibration measurement on aero gas turbine engines. Devi Priya, T, Kumar, S, Pratap, D, Shylaja, S, Satish, TN, Vishwanatha Rao, AN. In: Proceedings of the 11th international conference on engineering vibration 2015:1–13 pp. A benchmark for tip timing measurement of forced response in rotating bladed disks. Proc Inst Mech Eng Part G J Aerosp Eng 2008 222:497–506. Blade tip timing and strain gauge correlation on compressor blades. An experimental and computational investigation of a pulsed air-jet excitation system on a rotating bladed disk. Volume 1: compressors, fans and pumps turbines heat transfer combustion, fuels and emissions. In: Proceedings of the ASME 2017 gas turbine India conference. ![]() Aeroelastic flutter investigation and stability enhancement of a transonic axial compressor rotor using casing treatment. Purushothaman, K, Jeyaraman, SK, Pratap, A, Prasad Deshkulkarni, K. 32 years after the British midland Boeing 737 crash: what we learned 2021. In: IOP conference series: materials science and engineering(Vol. The influence of design parameters on the blade flutter boundaries. Abdukhakimov, F, Vedeneev, V, Kolotnikov, M, Makarov, P. ![]() Flutter and resonant vibration characteristics of engine blades. Research funding: No research funding provided.Ĭonflict of interest statement: The authors declare no conflicts of interest regarding this article.Īuthor contributions: All the authors have accepted responsibility for the entire content of this submitted manuscript and approved submission.ġ. Saurabh, who helped with instrumentation, engine testing, and the signal processing. They would also like to express their gratitude to Mr. The authors are grateful to the Director of the Gas Turbine Research Establishment (GTRE) in India and the Director of the National Aerospace Laboratories (NAL) in India for permitting them to participate in the research. This research provides a low-cost, easy alternative technique for measuring flutter during engine development testing. The approach’s estimated blade deflection was compared to measurements taken using a traditional tip timing method up to 7 mm and determined to be within 1% inaccuracy. The theory was tested using first-stage fan rotor blades that were fluttering in the first flexural mode (1F) and forming the second nodal diameter (2ND). The authors devised a mathematical model to explain signal spectrum components that feature both amplitude and angle modulation properties at the same time. Authors investigated a unique way for identifying, measuring, and validating flutter signature by assessing wall static pressure pulsations produced during blade tip transit across a casing mounted high bandwidth sensor during this research. ![]() Flutter signature capture from revolving blades is a challenging task that necessitates either a complicated strain gauge-based rotating instrumentation or a noncontact tip timing system. Hence, suitable flutter detection instrumentation is required during engine testing. Flutter, an aeroelastic blade vibration phenomena, experienced by the fan of an developmental aero gas turbine engine, result in blade failure.
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