Research Papers: Gas Turbines: Structures and Dynamics

Reduced Order Modeling for Multistage Bladed Disks With Friction Contacts at the Flange Joint

[+] Author and Article Information
Giuseppe Battiato

Politecnico di Torino,
Torino 10129, Italy
e-mail: giuseppe.battiato@polito.it

Christian M. Firrone

Politecnico di Torino,
Torino 10129, Italy
e-mail: christian.firrone@polito.it

Teresa M. Berruti

Politecnico di Torino,
Torino 10129, Italy
e-mail: teresa.berruti@polito.it

Bogdan I. Epureanu

Department of Mechanical Engineering,
University of Michigan,
Ann Arbor, MI 48109-2125
e-mail: epureanu@umich.edu

1Corresponding author.

Contributed by the Structures and Dynamics Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received July 4, 2017; final manuscript received August 31, 2017; published online January 3, 2018. Editor: David Wisler.

J. Eng. Gas Turbines Power 140(5), 052505 (Jan 03, 2018) (10 pages) Paper No: GTP-17-1273; doi: 10.1115/1.4038348 History: Received July 04, 2017; Revised August 31, 2017

Most aircraft turbojet engines consist of multiple stages coupled by means of bolted flange joints which potentially represent source of nonlinearities due to friction phenomena. Methods aimed at predicting the forced response of multistage bladed disks have to take into account such nonlinear behavior and its effect in damping blades vibration. In this paper, a novel reduced order model (ROM) is proposed for studying nonlinear vibration due to contacts in multistage bladed disks. The methodology exploits the shape of the single-stage normal modes at the interstage boundary being mathematically described by spatial Fourier coefficients. Most of the Fourier coefficients represent the dominant kinematics in terms of the well-known nodal diameters (standard harmonics), while the others, which are detectable at the interstage boundary, correspond to new spatial small wavelength phenomena named as extra harmonics. The number of Fourier coefficients describing the displacement field at the interstage boundary only depends on the specific engine order (EO) excitation acting on the multistage system. This reduced set of coefficients allows the reconstruction of the physical relative displacement field at the interface between stages and, under the hypothesis of the single harmonic balance method (SHBM), the evaluation of the contact forces by employing the classic Jenkins contact element. The methodology is here applied to a simple multistage bladed disk and its performance is tested using as a benchmark the Craig–Bampton ROMs of each single stage.

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Fig. 1

Interface and active DoF in the case of a bladed disk

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Fig. 2

h = 2 mode shape of a dummy blisk at the disk level: the displacement field at the blue circumference is described by the sum of increasing order spatial harmonics

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Fig. 3

Interstage boundary of a cyclic symmetric stage. Sectors and radial line segments are denoted by n and j, respectively [23].

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Fig. 4

1D Jenkins contact element with constant normal load N0 and tangential contact load fc acting on the ground

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Fig. 5

Multistage bladed disk full FE model

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Fig. 6

Normalized forced responses of the stage 1: α multistage ROM versus β multistage ROM

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Fig. 7

Normalized forced responses of the stage 2: α multistage ROM versus β multistage ROM




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