An efficient model order reduction technique for forced vibration analysis of a mistuned bladed disk with friction contact is presented. The present method applicable for small blade-to-blade mistuning, provides significant reduction in time without loss of accuracy for the nonlinear statistical analysis of mistuned bladed disks. This is achieved by obtaining a reduced order model of the mistuned bladed disks without generating its stiffness and mass matrices and considering the effect of mistuning on the static modes used in the reduction. This new approach can be interpreted as a hybrid of two existing techniques: Component mode mistuning (CMM) and a Dual model order reduction technique. The Dual method is a free interface based Componen...
An efficient method for analysis of nonlinear vibrations of mistuned bladed disk assemblies has been...
The effect of random blade mistuning on the dynamics of bladed disks is investigated. A reduced-orde...
Peer Reviewedhttp://deepblue.lib.umich.edu/bitstream/2027.42/76928/1/AIAA-2004-1686-437.pd
A new reduced order modeling technique for nonlinear vibration analysis of mistuned bladed disks wit...
A new reduced order modeling technique for nonlinear vibration analysis of mistuned bladed disks wit...
A new reduced order modeling technique for nonlinear dynamics of mistuned bladed disks with friction...
A new reduced order modelling technique based on Relative Cyclic Component Mode Synthesis (RCCMS) is...
In this paper, a pre-existing reduction technique suitable for the analysis of mistuned bladed disk ...
Bladed disks are used in many important engineering applications, including turbine engine rotors. T...
Bladed disks are used in many important engineering applications, including turbine engine rotors. T...
Forced response analysis of bladed disk assemblies plays a vital role in rotor blade design and has ...
The unavoidable existence of small differences between nominally identical sectors of bladed disks, ...
p. 1938-1950 A reduced-order model formulation is presented for examining the forced response of tun...
A new method for the dynamic analysis of mistuned bladed disks is presented. The method is based on ...
Nominally, a bladed disk assembly (single stage of a turbomachinery rotor) is a rotationally periodi...
An efficient method for analysis of nonlinear vibrations of mistuned bladed disk assemblies has been...
The effect of random blade mistuning on the dynamics of bladed disks is investigated. A reduced-orde...
Peer Reviewedhttp://deepblue.lib.umich.edu/bitstream/2027.42/76928/1/AIAA-2004-1686-437.pd
A new reduced order modeling technique for nonlinear vibration analysis of mistuned bladed disks wit...
A new reduced order modeling technique for nonlinear vibration analysis of mistuned bladed disks wit...
A new reduced order modeling technique for nonlinear dynamics of mistuned bladed disks with friction...
A new reduced order modelling technique based on Relative Cyclic Component Mode Synthesis (RCCMS) is...
In this paper, a pre-existing reduction technique suitable for the analysis of mistuned bladed disk ...
Bladed disks are used in many important engineering applications, including turbine engine rotors. T...
Bladed disks are used in many important engineering applications, including turbine engine rotors. T...
Forced response analysis of bladed disk assemblies plays a vital role in rotor blade design and has ...
The unavoidable existence of small differences between nominally identical sectors of bladed disks, ...
p. 1938-1950 A reduced-order model formulation is presented for examining the forced response of tun...
A new method for the dynamic analysis of mistuned bladed disks is presented. The method is based on ...
Nominally, a bladed disk assembly (single stage of a turbomachinery rotor) is a rotationally periodi...
An efficient method for analysis of nonlinear vibrations of mistuned bladed disk assemblies has been...
The effect of random blade mistuning on the dynamics of bladed disks is investigated. A reduced-orde...
Peer Reviewedhttp://deepblue.lib.umich.edu/bitstream/2027.42/76928/1/AIAA-2004-1686-437.pd