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Research Papers

Parametric Reduced Order Models for Bladed Disks With Mistuning and Varying Operational Speed

[+] Author and Article Information
Eric Kurstak

Gas Turbine Laboratory,
Department of Mechanical and
Aeronautical Engineering,
The Ohio State University,
Columbus, OH 43235
e-mail: kurstak.1@osu.edu

Ryan Wilber

Gas Turbine Laboratory,
Department of Mechanical and
Aeronautical Engineering,
The Ohio State University,
Columbus, OH 43235
e-mail: wilber.30@osu.edu

Kiran D'Souza

Gas Turbine Laboratory,
Department of Mechanical and
Aeronautical Engineering,
The Ohio State University,
Columbus, OH 43235
e-mail: dsouza.60@osu.edu

1Corresponding author.

Manuscript received July 16, 2018; final manuscript received July 26, 2018; published online March 8, 2019. Editor: Jerzy T. Sawicki.

J. Eng. Gas Turbines Power 141(5), 051018 (Mar 08, 2019) (9 pages) Paper No: GTP-18-1495; doi: 10.1115/1.4041204 History: Received July 16, 2018; Revised July 26, 2018

A considerable amount of research has been conducted to develop reduced order models (ROMs) of bladed disks that can be constructed using single sector calculations when there is mistuning present. A variety of methods have been developed to efficiently handle different types of mistuning ranging from small frequency mistuning, which can be modeled using a variety of methods including component mode mistuning (CMM), to large geometric mistuning, which can be modeled using multiple techniques including pristine rogue interface modal expansion (PRIME). Research has also been conducted on developing ROMs that can accommodate the variation of specific parameters in the reduced space; these models are referred to as parametric reduced order models (PROMs). This work introduces a PROM for bladed disks that allows for the variation of rotational speed in the reduced space. These PROMs are created by extracting information from sector models at three rotational speeds, and then the appropriate ROM is efficiently constructed in the reduced space at any other desired speed. This work integrates these new PROMs for bladed disks with two existing mistuning methods, CMM and PRIME, to illustrate how the method can be readily applied for a variety of mistuning methods. Frequencies and forced response calculations using these new PROMs are compared to the full order finite element calculations to demonstrate the effectiveness of the method.

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References

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Figures

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Fig. 1

Forced response curves showing the effects rotational speed has on system responses under an engine order 1 excitation for 0 RPM (–), 10,000 RPM (– –), and 20,000 RPM (⋯) rotational speed values

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Fig. 2

Flowchart showing steps to construct the U and KROM(p) matrices for a tuned system PROM

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Fig. 3

Flowchart showing steps to construct the U and KPROM(p) matrices for a PROM with small mistuning using CMM

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Fig. 4

Flowchart showing steps to construct the U and KPROM(p) matrices for a PROM with large mistuning using PRIME

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Fig. 5

Finite element model of 23 sector, pristine bladed disk

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Fig. 6

Percent relative error between the PROM and ANSYS FEM natural frequencies of a pristine system rotating at 17,500 RPM

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Fig. 7

Forced response comparison of the PROM (-) and ANSYS FEM (O) of a pristine system rotating at 17,500 RPM

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Fig. 8

Mistuning pattern applied to nominal system in the PROM-CMM reduction rotating at 17,500 RPM

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Fig. 9

Percent relative error between the PROM-CMM and ANSYS FEM natural frequencies of a pristine system with small mistuning rotating at 17,500 RPM

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Fig. 10

Forced response comparison of the PROM-CMM (-) and ANSYS FEM (O) of a pristine system with small mistuning rotating at 17,500 RPM under EO 1 and EO 20 excitations: (a) forced response under EO 1 excitation and (b) forced response under EO 20 excitation

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Fig. 11

Finite element model of 23 sector, rogue bladed disk with large mistuning in the form of 50% mass missing on one blade

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Fig. 12

Percent relative error between the PROM-PRIME and ANSYS FEM natural frequencies for a system with large mistuning rotating at 17,500 RPM

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Fig. 13

Forced response comparisons of the PROM-PRIME (-) and ANSYS FEM (O) for a system with 50% mass missing at one blade tip rotating at 17,500 RPM: (a) forced response of PROM-PRIME over the first mode family and (b) forced response of PROM-PRIME over the third mode family

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Fig. 14

Campbell diagram of a pristine system generated using PROM with engine order lines 7 (right most)–20 (left most)

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Fig. 15

Campbell diagram of a pristine system with small mistuning generated using PROM with engine order lines 7 (right most) to 20 (left most)

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