Journal articleJournal of the Brazilian Society of Mechanical Sciences and Engineering · July 1, 2026
In the turbomachinery design, non-synchronous vibration (NSV), observed primarily in the front stages of high-pressure compressors and fan blades, is a dangerous aeroelastic phenomenon resembling flutter response. However, typical flutter stability paramet ...
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Journal articleJournal of Turbomachinery · June 1, 2024
Over recent years, the aeroelastic problem of fan blades has become significantly serious due to the demand for high performance of aero-engines. To explore the aeroelastic issue of flutter, fan instability is represented by the aerodynamic damping. When t ...
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Journal articleJournal of Turbomachinery · August 1, 2023
A lack of reliable experimental data on transonic blade flutter in real turbomachines hampers the further improvement of computational design predictions for off-design operation regimes of newly-built machines. Acquiring unsteady pressure distribution on ...
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Journal articleJournal of Visualization · June 1, 2023
The paper deals with optical measurements of transonic flow past a five-blade compressor blade cascade. The middle blade of this cascade can be set to different incidence angles simulating its torsional deformation. Classical optical methods (shadowgraphy, ...
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Journal articleJournal of Engineering for Gas Turbines and Power · May 1, 2023
This paper is a continuation of previous papers by the authors that focuses on predicting the mistuned embedded rotor blade forced response. The compressor under consideration is a part of a 3.5stage rig located at Purdue University. Previously, the curren ...
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Journal articleJournal of Turbomachinery · April 1, 2023
Boundary-layer ingestion systems have the potential to improve propulsion efficiency using fluid with lower momentum near the airframe. However, they also bring variations in the velocity and total pressure, leading to a complex distortion of the flow at t ...
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Journal articleJournal of Turbomachinery · January 1, 2023
This paper builds upon a two-degree-of-freedom Van der Pol oscillator-based reducedorder model for studying the mechanisms around nonsynchronous vibrations (NSV) in turbomachinery. One degree tracks the fluid motion utilizing a combination of a traditional ...
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Journal articleJournal of Turbomachinery · March 1, 2022
This paper expands upon a multi-degree-of-freedom, Van der Pol oscillator used to model buffet and nonsynchronous vibrations (NSV) in turbines. Two degrees-of-freedom are used, a fluid tracking variable incorporating a Van der Pol oscillator and a classic ...
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Journal articleJournal of Turbomachinery · September 1, 2019
The aerodynamic interaction of upstream and downstream blade rows can have a significant impact on the forced response of the compressor. Previously, the authors carried out the forced response analysis of a three-row stator-rotor-stator (S1-R2-S2) configu ...
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Journal articleJournal of Engineering for Gas Turbines and Power · March 1, 2019
Accuracy when assessing mistuned forced response analyses is still a major concern. Since a fully coupled analysis is still very computational expensive, several simplifications and reduced-order models (ROMs) are carried out. The use of a reduction method ...
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Journal articleJournal of Turbomachinery · March 1, 2018
This paper is the second part of a two-part paper that presents a comprehensive study of the higher-order mode (HOM) mistuned forced response of an embedded rotor blisk in a multistage axial research compressor. The resonant response of the second-stage ro ...
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Journal articleJournal of Propulsion and Power · January 1, 2017
The flutter CFD calculations conducted in industry generally use a single-row, single-passage approach with a minimum of detailing to reduce the computational time as much as possible. The question arises of what level of detailing is necessary for accurat ...
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Journal articleJournal of Turbomachinery · June 1, 2016
This paper covers a comprehensive forced response analysis conducted on a multistage compressor and compared with the largest forced response experimental data set ever obtained in the field. The steady-state aerodynamic performance and stator wake predict ...
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Journal articleJournal of Turbomachinery · April 1, 2016
The three major aeroelastic issues in the turbomachinery blades of jet engines and power turbines are forced response, nonsynchronous vibrations, and flutter. Flutter primarily affects high-aspect ratio blades found in the fan, fore high-pressure compresso ...
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Journal articleJournal of Turbomachinery · March 1, 2016
The frequency mistuning that occurs due to manufacturing variations and wear and tear of the blades has been shown to significantly affect the flutter and forced response behavior of a blade row. While tuned computational fluid dynamics (CFD) analyses are ...
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Journal articleJournal of Fluids and Structures · February 1, 2016
This work presents a novel way to calculate the response amplitude of an elastically supported cylinder experiencing vortex-induced vibrations. The method couples a computational fluid dynamic (CFD) model of the shedding vortex flow to a structural model r ...
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Journal articleJournal of Fluids Engineering Transactions of the ASME · January 1, 2016
Vortex-induced vibration is a fluid instability where vortices due to secondary flows exert a periodic unsteady force on the elastic structure. Under certain circumstances, the shedding frequency can lock into the structure natural frequency and lead to li ...
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Journal articleJournal of Engineering for Gas Turbines and Power · May 1, 2015
The paper develops a reduced-order model of nonsynchronous vibration (NSV) using proper orthogonal decomposition (POD) methods. The approach was successfully developed and implemented, requiring between two and six POD modes to accurately predict computati ...
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Journal articleJournal of Engineering for Gas Turbines and Power · January 1, 2015
Successful, efficient turbine design requires a thorough understanding of the underlying physical phenomena. This paper investigates the flutter phenomenon of low pressure turbine (LPT) blades seen in aircraft engines and power turbines. Computational flui ...
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Journal articleJournal of Fluids and Structures · January 1, 2013
In this paper, the effect of aerodynamic asymmetries on the flutter characteristics of turbomachinery blades is investigated. Specifically, the present method is used to study the effect of leading edge blending in loaded and unloaded rotors. The unsteady ...
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Journal articleJournal of Turbomachinery · June 23, 2011
A new mechanism for fan stator vane failure in turbofan engines at high speed and high loading has been identified and reported in this paper. Highly destructive vane failures have been encountered at Honeywell in a development fan with composite stator va ...
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Journal articleProceedings of the ASME Turbo Expo · December 1, 2010
A new mechanism for fan stator vane failure in turbofan engines at high speed and high loading has been identified and reported in this paper. Highly destructive vane failures have been encountered at Honeywell in one of the development fans with composite ...
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Journal articleJournal of Propulsion and Power · January 1, 2010
In this paper we apply the harmonic balance technique to analyze an inlet guide vane and rotor interaction problem, and compare the computed flow solutions to existing experimental data. The computed results, which compare well with the experimental data, ...
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Journal articleProceedings of the ASME Turbo Expo · December 1, 2009
The "Tie-Dye" (TD) method is a well-known preliminary flutter design method for subsonic low pressure turbine (LPT) blades. In this paper, a study of 2D mode shape sensitivity using the TD-method for supersonic exit Mach numbers is presented. Using a harmo ...
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Journal articleJournal of Turbomachinery · October 1, 2009
Most of the existing mistuning research assumes that the aerodynamic forces on each of the blades are identical except for an interblade phase angle shift. In reality, blades also undergo asymmetric steady and unsteady aerodynamic forces due to manufacturi ...
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Journal articleJournal Of Turbomachinery-transactions Of The Asme · April 2004
A current preliminary design method for flutter of low pressure turbine blades and vanes only requires knowledge of the reduced frequency and mode shape (real). However many low pressure turbine (LPT) blade designs include a tip shroud that mechanically co ...
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Journal articleJournal of Turbomachinery · January 1, 1993
A frequent cause of turbomachinery blade failure is excessive resonant response. The most common excitation source is the nonuniform flow field generated by inlet distortion, wakes and7 or pressure disturbances from adjacent blade rows. The standard method ...
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Journal articleJournal of Vibration and Acoustics Transactions of the ASME · January 1, 1990
A procedure is outlined for determining the optimal design of friction dampers for high-speed turbomachinery blading. The procedure includes: An integration of bench test results with finite-element analysis and a single-mode blade model to ensure accuracy ...
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Journal articleJournal of Turbomachinery · January 1, 1989
An application of a simple aeroelastic model to an advanced supersonic axial flow fan is presented. Lane’s cascade theory is used to determine the unsteady aerodynamic loads. Parametric studies are performed to determine the effects of mode coupling, Mach ...
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Journal articleJournal of Engineering for Gas Turbines and Power · January 1, 1986
This paper deals with the stabilizing effects of dry friction on torsional blade flutter. A lumped parameter model with single degree of freedom per blade has been used to represent the rotor stage. The well-known cascade theories for incompressible and su ...
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Journal articleJournal of Engineering for Gas Turbines and Power · January 1, 1986
This paper uses a typical section model to investigate analytically the effect of mass balancing as applied to hollow, supersonic fan blades. A procedure to determine the best configuration of an internal balancing mass to provide flutter alleviation is de ...
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Journal articleJournal of Engineering for Gas Turbines and Power · January 1, 1985
The purpose ofthe research presented in this paper is to study the effect ofsweep on fan blade flutter by applying the analytical methods developed for aeroelastic analysis of advanced turboprops. Two methods are used. The first method utilizes an approxim ...
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Journal articleJournal of Engineering for Gas Turbines and Power · January 1, 1985
The experimental portion of a joint government/industry/university research study on the vibrational characteristics of twisted cantilevered plates is presented. The overall purpose of the research study was to assess the capabilities and limitations of ex ...
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Journal articleJournal of Propulsion and Power · January 1, 1985
An analytical model for investigating vibration and flutter of mistuned bladed-disk assemblies is presented. This model accounts for elastic, inertial, and aerodynamic coupling between bending and torsional motions of each individual blade, elastic and ine ...
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Journal articleInternational Journal for Numerical Methods in Engineering · January 1, 1985
Previously published literature shows widely different results for the free vibration frequencies of twisted cantilever plates. Inasmuch as it is important to know the vibration characteristics of turbomachinery blades, which may have considerable twist, i ...
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Journal articleJournal of Sound and Vibration · September 22, 1984
This work summarizes a comprehensive study made of the free vibrations of twisted, cantilevered plates of rectangular planform. Numerous theoretical and experimental investigations previously made by others have resulted in frequency results which disagree ...
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Journal articleNASA Technical Paper · May 1, 1984
The Lewis Research Center spin rig was constructed to provide experimental evaluation of analysis methods developed under the NASA Engine Structural Dynamics Program. Rotors up to 51 cm (20in. ) in diameter can be spun to 16,000 rpm up to 51 cm (20 in. ) i ...
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Journal articleJournal of Applied Mechanics Transactions ASME · January 1, 1984
The effect of pretwist and warping on the torsional vibration of short-aspect-ratio rotating beams is examined for application to the modeling ofturbofan, turboprop, and compressor blades. The equations of motion and the associated boundary conditions by u ...
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Journal article · January 1, 1984
The purpose of the research presented in this paper is to study the effect of sweep on fan blade flutter by applying the analytical methods developed for aeroelastic analysis of advanced turboprops. Two methods are used. The first method utilizes an approx ...
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Journal articleJournal of Engineering for Gas Turbines and Power · January 1, 1984
The effects of structural coupling on mistuned cascade flutter and response are analytically investigated using an extended typical section model. Previous work using two degree of freedom per blade typical section models has included only aerodynamic coup ...
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Journal articleTrans ASME J Engng Gas Turbines Power · January 1, 1984
The effect of sweep on fan blade flutter by applying the analytical methods developed for aeroelastic analysis of advanced turboprops was studied. Two methods are used. The first method utilizes an approximate structural model in which the blade is represe ...
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Journal articleNASA Technical Memorandum · January 1, 1984
The purpose of the research presented in this paper is to study the effect of sweep on fan blade flutter by applying the analytical methods developed for aeroelastic analysis of advance turboprops. Two methods are used. The first method utilizes an approxi ...
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Journal articleNASA Technical Memorandum · January 1, 1984
An analytical model for investigating vibration and flutter of mistuned bladed disk assemblies is presented. This model accounts for elastic, inertial and aerodynamic coupling between bending and torsional motions of each individual blade, elastic and iner ...
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Journal articleAIAA Journal · January 1, 1984
A set of aeroelastic equations describing the motion of an arbitrarily mistuned rotor with flexible, pretwisted, nonuniform blades is developed using an extended Hamilton's principle. The derivation of the equations has its basis in the geometric nonlinear ...
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Journal article · January 1, 1984
The purpose of the research presented in this paper is to study the effect of sweep on fan blade flutter by applying the analytical methods developed for aeroelastic analysis of advanced turboprops. Two methods are used. The first method utilizes an approx ...
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Journal articleNASA Technical Memorandum · January 1, 1984
An analytical model for investigating vibration and flutter of mistuned bladed disk assemblies is presented. This model accounts for elastic, inertial and aerodynamic coupling between bending and torsional motions of each individual blade, elastic and iner ...
Cite
Journal articleNASA Technical Paper · January 1, 1984
The Lewis Research Center spin rig was constructed to provide experimental evaluation of analysis methods developed under the NASA Engine Structural Dynamics Program. Rotors up to 51 cm (20in. ) in diameter can be spun to 16,000 rpm up to 51 cm (20 in. ) i ...
Cite
Journal articleNASA Technical Memorandum · January 1, 1984
The purpose of the research presented in this paper is to study the effect of sweep on fan blade flutter by applying the analytical methods developed for aeroelastic analysis of advance turboprops. Two methods are used. The first method utilizes an approxi ...
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Journal articleNASA Technical Memorandum · March 27, 1983
The effects of structural coupling on mistuned cascade flutter and response are analytically investigated using an extended typical section model. Previous work using two degree of freedom per blade typical section models has included only aerodynamic coup ...
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Journal articleJournal of Vibration and Acoustics Transactions of the ASME · January 1, 1983
An investigation of the effects of mistuning on flutter and forced response of a cascade in subsonic and supersonic flows is presented. The aerodynamic andstructural coupling between the bending and torsional motions and the aerodynamic coupling between th ...
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Journal articleNASA Technical Memorandum · January 1, 1983
The effects of structural coupling on mistuned cascade flutter and response are analytically investigated using an extended typical section model. Previous work using two degree of freedom per blade typical section models has included only aerodynamic coup ...
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Journal articleNASA Technical Memorandum · December 1, 1982
Experimental and analytical results are presented for a bending-torsion flutter phenomena encountered during wind-tunnel testing of a ten-bladed, advanced, high-speed propeller (turboprop) model with thin airfoil sections, high blade sweep, low aspect rati ...
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Journal articleNASA Tech Memo · May 10, 1982
A SET OF AEROELASTIC EQUATIONS DESCRIBING THE MOTION OF AN ARBITRARILY MISTUNED CASCADE WITH FLEXIBLE, PRETWISTED, NONUNIFORM BLADES IS DEVELOPED USING AN EXTENDED HAMILTON'S PRINCIPLE. A GENERAL EXPRESSION FOR FORESHORTENING OF A BLADE ISDERIVED AND IS EX ...
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Journal articleNASA Tech Memo · January 1, 1982
A SET OF AEROELASTIC EQUATIONS DESCRIBING THE MOTION OF AN ARBITRARILY MISTUNED CASCADE WITH FLEXIBLE, PRETWISTED, NONUNIFORM BLADES IS DEVELOPED USING AN EXTENDED HAMILTON'S PRINCIPLE. A GENERAL EXPRESSION FOR FORESHORTENING OF A BLADE ISDERIVED AND IS EX ...
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Journal articleNASA Technical Memorandum · January 1, 1982
Experimental and analytical results are presented for a bending-torsion flutter phenomena encountered during wind-tunnel testing of a ten-bladed, advanced, high-speed propeller (turboprop) model with thin airfoil sections, high blade sweep, low aspect rati ...
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Journal articleAmerican Society of Mechanical Engineers (Paper) · December 1, 1981
An investigation of the effects of mistuning on flutter and forced response of a cascade in subsonic and supersonic flows is presented. The aerodynamic and structural coupling between the bending and torsional motions and the aerodynamic coupling between t ...
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Journal articleNASA Technical Memorandum · December 1, 1981
An investigation of the effects of mistuning on flutter and forced response of a cascade in subsonic and supersonic flows is presented. The aerodynamic and structural coupling between the bending and torsional motions and the aerodynamic coupling between t ...
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Journal article · January 1, 1981
The results of an investigation of the effects of mistuning on flutter and forced response of a cascade in subsonic and supersonic flows is presented. The aerodynamic and structural coupling between the bending and torsional motions and the aerodynamic cou ...
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Journal articleNASA Technical Memorandum · January 1, 1981
An investigation of the effects of mistuning on flutter and forced response of a cascade in subsonic and supersonic flows is presented. The aerodynamic and structural coupling between the bending and torsional motions and the aerodynamic coupling between t ...
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Journal articleAmerican Society of Mechanical Engineers (Paper) · January 1, 1981
An investigation of the effects of mistuning on flutter and forced response of a cascade in subsonic and supersonic flows is presented. The aerodynamic and structural coupling between the bending and torsional motions and the aerodynamic coupling between t ...
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Journal articleundefined · January 1, 1981
The results of an investigation of the effects of mistuning on flutter and forced response of a cascade in subsonic and supersonic flows is presented. The aerodynamic and structural coupling between the bending and torsional motions and the aerodynamic cou ...
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Journal articleJournal of Sound and Vibration · June 22, 1980
Numerical solutions are presented for the fundamental natural frequency and mode shape of a rectangular plate loaded by in-plane hydrostatic forces for a wide variety of aspect ratios, boundary conditions, and load magnitudes. All six possible combinations ...
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Journal articleJournal of Aircraft · January 1, 1977
Directionally solidifed, air-cooled turbine blades present new challenges to the structural design analyst. This paper describes an investigation of turbine blade failures encountered during a recent engine development program. The effect of wall tolerance ...
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Journal articleJournal of Aircraft · January 1, 1975
The conical shell element with nonsymmetric loading and displacement capabilities has excellent possibilities for application to engine static structures. The major benefit would be a dramatic reduction in computer time as compared with a plate model, howe ...
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