An N-S Simulation of Stall Cell Behavior in a 2-D Compressor Rotor-Stator System at Various Loads

Outa, Eisuke; Kato, Dai; Chiba, Kaoru

doi:10.1115/94-gt-257

Cited by 13 publications

(6 citation statements)

References 10 publications

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“…The second is flow fields simulation, which directly solves Navier-Stokes (N-S) equations or Euler equations. Outa et al [9] and He [10] carried out a twodimensional N-S simulation. Outa analysed the stall cells structure and characteristics at different conditions by using a simple throttling valve at stage outlet.…”

Section: Introductionmentioning

confidence: 99%

Numerical simulations of stall inside a centrifugal compressor

Guo

Chen²,

Zhu

et al. 2007

Proceedings of the Institution of Mechanical Engineers, Part A:

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This paper presents a numerical simulation of stall flow phenomenon inside a turbocharger centrifugal compressor with vaneless diffuser. Three-dimensional Reynolds averaged compressible Navier-Stokes equations were solved with k-ε turbulence model using computational fluid dynamics software CFX. Entire geometry of the compressor, including the impeller, vaneless diffuser, and volute housing were included in the simulation. The stage performance curve was obtained using steady and unsteady calculations and compared with experimental results. The unsteady flow simulation was performed at reduced mass flowrates (compressor stall region) with a plenum chamber model added at the compressor housing outlet. The results show that there is a distinct stall frequency at the given compressor speed. The amplitude of the static pressure oscillation at this frequency in the diffuser is increased with reduction in compressor mass flow. The stall frequency is only marginally affected by the compressor mass flowrate. Time varying flow fields in the diffuser and in the volute indicate that there is a circumferential standing wave inside the volute. It is proposed that the volute behaves like a tuned pipe resonator and this dictates the stall frequency. The stall is also characterized by a periodically reversing flow at the centre of the volute discharge cross-section.

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Section: Introductionmentioning

confidence: 99%

Numerical simulations of stall inside a centrifugal compressor

Guo

Chen²,

Zhu

et al. 2007

Proceedings of the Institution of Mechanical Engineers, Part A:

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“…For steady RANS simulations, the static pressure is imposed under the condition of radial equilibrium. For time-dependent RANS, a macroscopic pressure resistance model defined in Equation (3) is applied at the outlet boundary in order to model the pressure drop during the stall inception process [27,28]. where c t is the pressure resistance coefficient of the downstream throttle valve which is used in the experiment to set the operating condition of the compressor rotor, = ρ is the mass-averaged fluid density at the computational outlet, and = u a is the mass-averaged axial velocity at the computational outlet.…”

Section: Methodsmentioning

confidence: 99%

Numerical Optimization of a Stall Margin Enhancing Recirculation Channel for an Axial Compressor

Kawase

Rona

2019

Fluids

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A proof of concept is provided by computational fluid dynamic simulations of a new recirculating type casing treatment. This treatment aims at extending the stable operating range of highly loaded axial compressors, so to improve the safety of sorties of high-speed, high-performance aircraft powered by high specific thrust engines. This casing treatment, featuring an axisymmetric recirculation channel, is evaluated on the NASA rotor 37 test case by steady and unsteady Reynolds Averaged Navier Stokes (RANS) simulations, using the realizable k-ε model. Flow blockage at the recirculation channel outlet was mitigated by chamfering the exit of the recirculation channel inner wall. The channel axial location from the rotor blade tip leading edge was optimized parametrically over the range −4.6% to 47.6% of the rotor tip axial chord c z . Locating the channel at 18.2% c z provided the best stall margin gain of approximately 5.5% compared to the untreated rotor. No rotor adiabatic efficiency was lost by the application of this casing treatment. The investigation into the flow structure with the recirculating channel gave a good insight into how the new casing treatment generates this benefit. The combination of stall margin gain at no rotor adiabatic efficiency loss makes this design attractive for applications to high-speed gas turbine engines.

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“…Two distinctive routes to severe instabilities are admitted: the long-scale (or modal) inception and the short-length scale (or spike type) inception (for example Moore and Greitzer [1,2], Camp and Day [3], Outa et al [4], Vo et al [5], Justen et al [6]). Depending on the compressor and depending on the rotation speed for a given compressor, it is not clear to anticipate which type of wave drives the compression system into surge.…”

Section: Introductionmentioning

confidence: 98%