A high speed 1–1/2 axial compressor stage is simulated in this paper using an unsteady Reynolds-averaged Navier–Stokes (URANS) solver for a full-annulus configuration to capture its nonsynchronous vibration (NSV) flow excitation with rigid blades. A third-order weighted essentially nonoscillatory scheme for the inviscid flux and a second-order central differencing for the viscous terms are used to resolve nonlinear unsteady fluid flows. A fully conservative rotor/stator sliding boundary condition (BC) is employed with multiple-processor capability for rotor/stator sliding interface that accurately captures unsteady wake propagation between the rotor and stator blades while conserving fluxes across the rotor/stator interfaces. The predicted dominant frequencies using the blade tip response signals are not harmonic to the engine order, which is the NSV excitation. The simulation is based on a rotor blade with a 1.1% tip-chord clearance. Comparison with the previous 1/7 annulus simulations show that the time-shifted phase-lag BCs used in the 1/7 annulus are accurate. For most of the blades, the NSV excitation frequency is 6.2% lower than the measurement in the rig test, although some blades displayed slightly different NSV excitation frequencies. The simulation confirms that the NSV is a full annulus phenomenon. The instability of the circumferential traveling vortices in the vicinity of the rotor tip due to the strong interaction of incoming flow is the main cause of the NSV excitation. This instability is present in all blades of the rotor annulus. For circumferentially averaged parameters like total pressure ratio, NSV is observed to have an effect on the radial profile, particularly at radial locations above 70% span. A design with a lower loading of the upper blade span and a higher loading of the midblade spans is recommended to mitigate or remove NSV.
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March 2018
Research-Article
Full-Annulus Simulation of Nonsynchronous Blade Vibration Excitation of an Axial Compressor
Daniel Espinal,
Daniel Espinal
Pratt & Whitney,
East Hartford, CT 06118
East Hartford, CT 06118
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Hong-Sik Im,
Hong-Sik Im
Doosan ATS America,
11360 Jog Rd,
Palm Beach Gardens, FL 33418
11360 Jog Rd,
Palm Beach Gardens, FL 33418
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Ge-Cheng Zha
Ge-Cheng Zha
Professor
Department of Mechanical and
Aerospace Engineering,
University of Miami,
Coral Gables, FL 33124
e-mail: gzha@miami.edu
Department of Mechanical and
Aerospace Engineering,
University of Miami,
Coral Gables, FL 33124
e-mail: gzha@miami.edu
Search for other works by this author on:
Daniel Espinal
Pratt & Whitney,
East Hartford, CT 06118
East Hartford, CT 06118
Hong-Sik Im
Doosan ATS America,
11360 Jog Rd,
Palm Beach Gardens, FL 33418
11360 Jog Rd,
Palm Beach Gardens, FL 33418
Ge-Cheng Zha
Professor
Department of Mechanical and
Aerospace Engineering,
University of Miami,
Coral Gables, FL 33124
e-mail: gzha@miami.edu
Department of Mechanical and
Aerospace Engineering,
University of Miami,
Coral Gables, FL 33124
e-mail: gzha@miami.edu
1Corresponding author.
Manuscript received September 26, 2016; final manuscript received October 27, 2017; published online December 27, 2017. Assoc. Editor: Li He.
J. Turbomach. Mar 2018, 140(3): 031008 (12 pages)
Published Online: December 27, 2017
Article history
Received:
September 26, 2016
Revised:
October 27, 2017
Citation
Espinal, D., Im, H., and Zha, G. (December 27, 2017). "Full-Annulus Simulation of Nonsynchronous Blade Vibration Excitation of an Axial Compressor." ASME. J. Turbomach. March 2018; 140(3): 031008. https://doi.org/10.1115/1.4038337
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