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Research Papers

Effect of Scaling of Blade Row Sectors on the Prediction of Aerodynamic Forcing in a Highly Loaded Transonic Compressor Stage

[+] Author and Article Information
María A. Mayorca, Damian M. Vogt, Torsten H. Fransson

 Royal Institute of Technology, Heat and Power Technology, S-100 44 Stockholm, Sweden

Jesús A. De Andrade

Laboratorio de Conversión de Energía Mecánica, Universidad Simón Bolívar, 1080 Sartenejas, Miranda, Venezuela

Hans Mårtensson

 Volvo Aero Corporation, S-461 81 Trollhättan, Sweden

J. Turbomach 133(2), 021013 (Oct 22, 2010) (10 pages) doi:10.1115/1.4000579 History: Received July 21, 2009; Revised July 30, 2009; Published October 22, 2010; Online October 22, 2010

An investigation of the sensitivity of a geometrical scaling technique on the blade forcing prediction and mode excitability has been performed. A stage of a transonic compressor is employed as a test object. A scaling ratio is defined, which indicates the amount of scaling from the original geometry. Different scaling ratios are selected and 3D Navier–Stokes unsteady calculations completed for each scaled configuration. A full-annulus calculation (nonscaled) is performed serving as reference. The quantity of interest is the generalized force, which gives a direct indication of the mode excitability. In order to capture both up- and downstream excitation effects, the mode excitability has been assessed on both rotor and stator blades. The results show that the first harmonic excitation can be predicted well for both up- and downstream excitations using moderate amounts of scaling. On the other hand, the predictions of second harmonic quantities do show a higher sensitivity to scaling for the investigated test case.

Copyright © 2011 by American Society of Mechanical Engineers
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References

Figures

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Figure 1

Investigated compressor stage

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Figure 2

Compressor map (18); selected operating point for unsteady analysis highlighted

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Figure 3

Block numbers of one passage

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Figure 4

FE mesh of rotor and stator blades; restrain boundary conditions highlighted

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Figure 5

Multiblock mesh at tip of scaled configuration R3S7 for unsteady calculations

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Figure 6

Steady state Mach number contours at different spans; nonscaled model

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Figure 7

Pressure and suction sides; steady state static pressure

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Figure 8

Unsteady calculation convergence; rotor (above) and stator (below); convergence samples highlighted

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Figure 9

Rotor (left) and stator (right) loadings at 10%, 50%, and 90% span from top to bottom

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Figure 10

Normalized generalized force for the first 28 rotor modes; first harmonic excitation (51EO)

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Figure 11

Error in the prediction of normalized generalized force on rotor of mode 6; first harmonic excitation (51EO)

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Figure 12

rms deviation of normalized generalized force on rotor; first harmonic (51EO)

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Figure 13

Normalized generalized forces of the first 15 stator modes; first harmonic

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Figure 14

Error in the prediction of normalized generalized force on stator of mode 2; first harmonic excitation (23EO)

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Figure 15

rms deviation of normalized generalized force on stator; first harmonic (23EO)

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Figure 16

Normalized generalized forces of the first 15 stator modes; second harmonic (46EO)

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Figure 17

rms deviation of normalized generalized force on stator; second harmonic (46EO)

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Figure 18

Pressure amplitude at different rotor spans; first harmonic; nonscaled model

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Figure 19

Distributed generalized force contours; first harmonic forces projected on rotor mode 6; pressure side

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Figure 20

Pressure amplitude at different stator spans; first harmonic; nonscaled model

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Figure 21

Generalized force contours from the first harmonic forces on the stator; mode 2

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Figure 22

Space-time map at 50% span; nonscaled

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Figure 23

Space-time map at 50% span; case R4S9; relative phase of different scaled cases indicated

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