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Research Papers

Mechanism of Nonsynchronous Blade Vibration in a Transonic Compressor Rig

[+] Author and Article Information
Daniel Möller

Gas Turbines and Aerospace Propulsion,
Technische Universität Darmstadt,
Darmstadt 64287, Germany
e-mail: moeller@glr.tu-darmstadt.de

Maximilian Jüngst, Felix Holzinger, Christoph Brandstetter, Heinz-Peter Schiffer

Gas Turbines and Aerospace Propulsion,
Technische Universität Darmstadt,
Darmstadt 64287, Germany

Sebastian Leichtfuß

TurboScience GmbH,
Darmstadt 64287, Germany

1Corresponding author.

Manuscript received October 30, 2015; final manuscript received June 8, 2016; published online August 2, 2016. Assoc. Editor: Rakesh Srivastava.

J. Turbomach 139(1), 011002 (Aug 02, 2016) (10 pages) Paper No: TURBO-15-1240; doi: 10.1115/1.4034029 History: Received October 30, 2015; Revised June 08, 2016

This paper presents a numerical study on blade vibration for the transonic compressor rig at the Technische Universität Darmstadt (TUD), Darmstadt, Germany. The vibration was experimentally observed for the second eigenmode of the rotor blades at nonsynchronous frequencies and is simulated for two rotational speeds using a time-linearized approach. The numerical simulation results are in close agreement with the experiment in both cases. The vibration phenomenon shows similarities to flutter. Numerical simulations and comparison with the experimental observations showed that vibrations occur near the compressor stability limit due to interaction of the blade movement with a pressure fluctuation pattern originating from the tip clearance flow. The tip clearance flow pattern travels in the backward direction, seen from the rotating frame of reference, and causes a forward traveling structural vibration pattern with the same phase difference between blades. When decreasing the rotor tip gap size, the mechanism causing the vibration is alleviated.

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References

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Figures

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Fig. 1

Layout of the transonic compressor rig at TUD

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Fig. 2

A 1.5-stage compressor configuration with VIGV, rotor, and stator (from left to right)

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Fig. 3

Single-passage mesh for the 1.5-stage compressor (every second grid line is shown)

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Fig. 4

First two eigenmodes of the rotor blades

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Fig. 5

Compressor characteristics from experiment and simulation

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Fig. 6

Relative Mach number contour and isolines of entropy near the blade tip from simulations at compressor stability limit

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Fig. 7

Spectrogram of WPT and SG signal during transient measurement at stability limit for N1, IA1

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Fig. 8

Spectrogram of WPT and SG signal during transient measurement at stability limit for N2, IA2

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Fig. 9

Aerodynamic damping versus ND for speed lines N1, IA1 and N2, IA2 at stability limit and aerodynamic damping versus prescribed modal displacement amplitude for N1, IA1 and ND 8 (least stable)

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Fig. 10

Aerodynamic damping per unit area and unsteady blade pressure amplitude for nominal speed N1 and ND 8 (least stable)

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Fig. 11

Aerodynamic damping per unit area and unsteady blade pressure amplitude for nominal speed N1 and ND 3 (most stable)

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Fig. 12

Pressure fluctuation corresponding to M2 frequency at casing above rotor from experiment and simulation for nominal speed N1 with ND 8 (least stable)

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Fig. 13

Streamlines impinging on excitation region at blade PS near the LE for nominal speed N1

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Fig. 14

Aerodynamic damping per unit area and unsteady blade pressure amplitude for part speed N2 and ND 6 (least stable)

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Fig. 15

Pressure fluctuation corresponding to M2 frequency at casing above rotor from experiment and simulation for part speed N2 with ND 6 (least stable)

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Fig. 16

Incidence-driven flow separation at blade SS near the LE at around 80% radial height (velocity vectors are scaled to uniform length)

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Fig. 17

Damping contribution of each rotor blade toward aerodynamic damping for ND 8 (case N1) and ND 6 (case N2)

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Fig. 18

Compressor characteristics for three tip gap sizes at nominal speed N1

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Fig. 19

Aerodynamic damping versus ND at the leftmost operating point on the speedline for three tip gap sizes

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Fig. 20

Damping contribution of each rotor blade toward aerodynamic damping for the least stable ND of different tip gap sizes

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Fig. 21

Aerodynamic damping per unit area and unsteady blade pressure amplitude for small rotor gap and ND 6 (least stable)

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