Mechanism of Nonsynchronous Blade Vibration in a Transonic Compressor Rig

Möller, Daniel; Jüngst, Maximilian; Holzinger, Felix; Brandstetter, Christoph; Schiffer, Heinz-Peter; Leichtfuß, Sebastian

doi:10.1115/1.4034029

Cited by 23 publications

(15 citation statements)

References 16 publications

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“…For the rotor under investigation, nonsynchronous vibrations have been measured across the speed range. A numerical study, using timelinearised computational fluid dynamics, has recently linked these vibrations to the convective transport of tip leakage fluid in the tip region (Möller et al, 2016).…”

Section: Introductionmentioning

confidence: 99%

PIV measurements of the transient flow structure in the tip region of a transonic compressor near stability limit

Brandstetter

Schiffer

2018

J. Glob. Power Propuls. Soc.

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The flow structures in an axial compressor that lead to short-length scale stall inception are investigated using optical measurements in a high-speed one and a half stage compressor. During transient throttling procedures, velocity was measured in a tangential plane at 92% channel height, intersecting the tip leakage vortex. The results show large scale disturbances of the secondary flow structure, which results from unsteady breakdown of the tip leakage vortex. It was possible to resolve spill forward several revolutions before the occurrence of rotating stall. This effect leads to local flow separations on the blade suction side and the development of radial vortex structures. The vortices are transported to the adjacent blade and cause further separations. Both effects are described in literature but were measured directly for the first time in a transonic compressor in this investigation. They are visualized for several time steps during transient throttling maneuvers and compared to blade vibration amplitudes. During the final phase before rotating stall occurs, asynchronous blade vibrations correlate with axial velocity in the region around the blade leading edge.

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Section: Introductionmentioning

confidence: 99%

PIV measurements of the transient flow structure in the tip region of a transonic compressor near stability limit

Brandstetter

Schiffer

2018

J. Glob. Power Propuls. Soc.

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“…Conducting experimental investigations, Holzinger (2017) describes coupling conditions for aerodynamic and structural propagating waves. The link between aerodynamic waves and vibration pattern of a BLISK can also be shown in numerical investigations, for example by Möller et al (2017) as well as Möller and Schiffer (2020).…”

Section: Introductionmentioning

confidence: 70%

“…In the nominal stage setup, the investigated BLISK rotor suffers 1T-NSV at the vicinity of its stability limit, as for example shown by Holzinger (2017) and Möller et al (2017).…”

Section: Global Trendsmentioning

confidence: 85%

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Effects of Varying Inlet Guide Vane Pattern on Aerodynamic Mistuning in Transonic Compressors

Franke¹,

Foret²,

Klausmann³

et al. 2020

Proceedings of Global Power &Amp; Propulsion Society

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This paper investigates the effects of a 1.5-stage transonic axial compressor with applied aerodynamic mistuning via circumferential variation of the inlet guide vane stagger angle. The experiments were carried out at the Darmstadt Transonic Compressor at Technical University of Darmstadt. The test rig represents a modern front stage high-pressure compressor of a jet engine. Using extensive steady and unsteady instrumentation, the global compressor characteristics and performance as well as the transient behavior, focusing on aerodynamic and aeromechanic phenomena, are analyzed.In order to suppress non-synchronous blade vibration of the BLISK rotor, triggered by modal pattern of aerodynamic disturbances, asymmetric rotor inflow conditions are applied via circumferential pattern of varying pre-swirl, given by the inlet guide vane stagger angle. The experimental study provides proof of concept and snapshot measurements regarding global performance as well as steady and unsteady aerodynamic effects. Comparing different aerodynamic mistuning pattern, the influence on performance, circumferential flow variation, synchronous vibration as well as the behavior during stall inception varies. For all configurations, the circumferential variation of the rotors operating condition is evident within the radial and circumferential aerodynamics as well as unsteady flow at the rotor tip. These findings provide similarities to effects presented for asymmetric casing geometries and related mistuning capabilities.

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“…To clarify the phenomenon of multiple NDs, further investigations of other SG and WPT sensor combinations are crucial. As indicated by Möller et al [15] and Stapelfeldt and Brandstetter [16], this phenomenon should also be investigated considering flutter criteria.…”

Section: Discussionmentioning

confidence: 94%

Experimental Aerodynamic and Aeroelastic Investigation of a Highly-Loaded 1.5-Stage Transonic Compressor with Tandem Stator

Foret

Franke

Klausmann

et al. 2021

IJTPP

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This paper experimentally investigates a highly-loaded 1.5-stage transonic axial compressor, which comprises a variable inlet guide vane, a BLISK rotor, and a variable stator in tandem arrangement. A detailed comparison between the newly designed compressor stage and a reference stage with a conventional stator design was conducted by using extensive instrumentation. Thus, steady and unsteady phenomena—focusing on the aerodynamic and aeroelastic behavior—were analyzed. Due to the new stator vane design, a higher aerodynamic stator vane loading was pursued, while the vane count was reduced. This, in turn, allowed a rotor design with an increased work coefficient. This experimental study revealed several effects of the optimized compressor stage in terms of both performance and the corresponding aerodynamics, as well as the aeroelastic behavior.

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Mechanism of Nonsynchronous Blade Vibration in a Transonic Compressor Rig

Cited by 23 publications

References 16 publications

PIV measurements of the transient flow structure in the tip region of a transonic compressor near stability limit

PIV measurements of the transient flow structure in the tip region of a transonic compressor near stability limit

Effects of Varying Inlet Guide Vane Pattern on Aerodynamic Mistuning in Transonic Compressors

Experimental Aerodynamic and Aeroelastic Investigation of a Highly-Loaded 1.5-Stage Transonic Compressor with Tandem Stator

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