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contributor authorFellows, David W.
contributor authorIskandar, Vincent
contributor authorBodony, Daniel J.
contributor authorMcGowan, Ryan C.
contributor authorKang, Sang-Guk
contributor authorPope, Aaron J.
contributor authorKweon, Chol-Bum M.
date accessioned2023-08-16T18:11:44Z
date available2023-08-16T18:11:44Z
date copyright4/3/2023 12:00:00 AM
date issued2023
identifier issn0889-504X
identifier otherturbo_145_8_081004.pdf
identifier urihttp://yetl.yabesh.ir/yetl1/handle/yetl/4291595
description abstractAircraft intermittent combustion engines often incorporate turbochargers adapted from ground-based applications to improve their efficiency and performance. These turbochargers can operate at off-design conditions and experience blade failures brought on by aerodynamic-induced blade resonances. A reduced-order model of the aeroelastic response of general fluid–structural configurations is developed using the Euler–Lagrange equation informed by numerical data from uncoupled computational fluid dynamic (CFD) and computational structural dynamic calculations. The structural response is derived from a method of assumed-modes approach. The unsteady fluid response is described by a modified version of piston theory that approximates the local transient pressure fluctuation in conjunction with steady CFD solution data. The reduced-order model is first applied to a classical panel flutter scenario and found to predict a flutter boundary that compares favorably to the boundary identified by existing theory and experimental data. The model is then applied to the high-pressure turbine of a dual-stage turbocharger. The model predictions are shown to reliably determine the lack of turbine blade flutter and rudimentary damping comparisons are performed to assess the ability of the model to ascertain the susceptibility of the turbine to forced response. Obstacles associated with the current experimental state of the art that impinge upon further numerical validation are discussed.
publisherThe American Society of Mechanical Engineers (ASME)
titleA Method for Predicting the Aeroelastic Response of Radial Turbomachines
typeJournal Paper
journal volume145
journal issue8
journal titleJournal of Turbomachinery
identifier doi10.1115/1.4057062
journal fristpage81004-1
journal lastpage81004-12
page12
treeJournal of Turbomachinery:;2023:;volume( 145 ):;issue: 008
contenttypeFulltext


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