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TECHNICAL PAPERS

Blade Aerodynamic Damping Variation With Rotor-Stator Gap: A Computational Study Using Single-Passage Approach

[+] Author and Article Information
H. D Li, L. He

School of Engineering, University of Durham, Durham DH1 3LE, UK

J. Turbomach 127(3), 573-579 (Mar 01, 2003) (7 pages) doi:10.1115/1.1928932 History: Received December 01, 2002; Revised March 01, 2003

One of the outstanding issues in turbomachinery aeromechanic analysis is the intrarow interaction effects. The present work is aimed at a systematic examination of rotor-stator gap effects on blade aerodynamic damping by using a three-dimensional (3D) time-domain single-passage Navier-Stokes solver. The method is based on the upwind finite volume discretization and the single-passage shape-correction approach with enhanced accuracy and efficiency for unsteady transonic flows prediction. A significant speedup (by a factor of 20) over to a conventional whole annulus solution has been achieved. A parametric study with different rotor-stator gaps (56%–216% rotor tip chord) for a 3D transonic compressor stage illustrates that the reflection from an adjacent stator row can change rotor aerodynamic damping by up to 100% depending on the intrarow gap spacing. Furthermore, this rotor aerodamping dependency on the intrarow gap seems also to be affected by the number of stator blades. The predicted nonmonotonic relationship between the rotor blade aerodynamic damping and the gap spacing suggests the existence of an optimum gap regarding rotor flutter stability and/or forced response stress levels.

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Copyright © 2005 by American Society of Mechanical Engineers
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Figures

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Figure 1

Single-passage domain and implementation of the phase-shift periodicity

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Figure 2

First-harmonic pressure jump coefficient distribution (Namba case) (AUSMD/V: upwind scheme, Namba: semi-analytical solution)

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Figure 3

Computational mesh on the meridional plane (ECLcompressor)

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Figure 4

Comparison of static pressure distributions at inlet and exit of the rotor row

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Figure 5

FE mesh for mode analysis

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Figure 6

Vibratory displacement (mode shape) of the first torsion mode

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Figure 7

Aerodamping coefficients of an isolate vibrating rotor

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Figure 8

Comparison of axial unsteady force time histories on rotor (in vibration) and stator blades (●Single passage solution, —Multipassage solution)

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Figure 9

Spectrum of unsteady axial forces on rotor and stator blades (ECL compressor stage, multi-passage solution; ωvib - rotor vibration freq., ωs - stator blade passing freq., ωR - rotor blade passing freq, ωvs - rotor vibration frequency shifted in stator frame)

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Figure 10

Validation of aerodamping calculations using the single-passage solver for different rotor-stator gaps (3D ECL compressor, blade counts 19:20)

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Figure 11

Rotor aerodynamic damping variation with rotor-stator gap spacing

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