An approximation for fully stalled cascades

Moses, H. L.; Thomason, S. B.

doi:10.2514/3.22865

Cited by 13 publications

(6 citation statements)

References 1 publication

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“…Whenever it is satisfied, the loss coefficient and deviation angle at the corresponding blade row exit conditions are obtained from the stall model of Moses and Thomason. 29…”

Section: Compressor Modelmentioning

confidence: 99%

Reduced order modelling of full-span rotating stall for the flow control simulation of axial compressors

Ferlauto

Taddei

2015

Proceedings of the Institution of Mechanical Engineers, Part A:

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A 2D mean-radius reduction of the flow inside an axial compressor is proposed here as basic model for long-term simulations of active control strategies. In fact, research on active control of compressor instabilities is still based on the 0-D lumped volume approach of Moore and Greitzer, 1,2 with enhancements, or on one-dimensional axial flow models. In the present work, the dynamics of the compressor flow instabilities is represented in both the axial and peripheral directions. Although this intermediate-level analysis cannot capture fully 3D aspects of rotating stall inception and the part-span stall, it has shown to include a wide variety of details with respect to simpler models, while it still retains computational requirements that allow for the long-term simulation of an entire compression system. In this framework, the paper focuses on the derivation of a flow model that can mimic the onset and the development of the instabilities leading the compressor to full-span rotating stall. The flow inside the compressor is solved by means of two-dimensional Euler equations whereas the effects of blade rows are modelled by quasi-steady actuator disks. The characteristic-based flux treatment on the actuator disk sides ensures a correct propagation of the wave signals. Therefore, flow perturbations can be followed until they lead to instabilities within the flow field. Both small and large amplitude disturbances are treated. Aerodynamic instabilities are numerically investigated and compared to experimental results. The numerical technique has been validated against available experiments on NASA Rotor 1B and against numerical and experimental data on the throttling of the BR710 multi-stage compressor rig.

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“…Whenever it is satisfied, the loss coefficient and deviation angle at the corresponding blade row exit conditions are obtained from the stall model of Moses and Thomason. 29…”

Section: Compressor Modelmentioning

confidence: 99%

Reduced order modelling of full-span rotating stall for the flow control simulation of axial compressors

Ferlauto

Taddei

2015

Proceedings of the Institution of Mechanical Engineers, Part A:

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“…For unstalled direct flow, the curves can be evaluated by a meanline method or, when the complete geometrical data are available, by a through-flow method (Massardo et al, 1990). The model utilized for reverse flow calculation is based on information reported in the literature (Carneal, 1990;Gamache, 1985;Koff and Greitzer, 1986;Moses and Thomason, 1986). The reverse flow model was discussed in depth by Massardo et al (1996).…”

Section: Mathematical Modelmentioning

confidence: 99%

Stage performance influence on dynamic simulation of gas turbine compressors

Massardo

Giusto

Ghiglino

1997

Aircraft Engineering and Aerospace Technology

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Analyses a stage-by-stage model to simulate the dynamic response of compression systems operating with axial multistage compressors. The compressor model is coupled with two different downstream volume (plenum) representations: the first is zero-dimensional and the second is one-dimensional. Both dynamic models utilize complete stage performance curves (direct unstalled flow, stalled flow and back flow) obtained through experimental investigation, or from theoretical analysis based on turbomachinery geometry and semiempirical considerations. Analyses in depth the results of the dynamic simulations, obtained utilizing both methods, compared to the experimental data reported in the literature, and finally compares one to the other through a fast Fourier transformer (FFT) analysis.

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“…Righi et al [19,20] established the three-dimensional model ACRoSS, where the calculation of the source term extended the assumptions of Longley [8] et al and can be used to calculate rotating stall and surge of the multistage compressor. Zeng [21] et al developed a new body-force model to capture the three-dimensional and unsteady features of stall and surge in compressors with Thomason and Moses's model [22].…”

Section: Introductionmentioning

confidence: 99%

“…There are few studies related to the loss coefficient and deviation angle during stall and reverse flow. Thomason and Moses [22] obtained the deviation angle and loss coefficient of the separation flow under the large attack angle by some assumptions. Tauveron [23] proposed a new correlation to estimate the steady-state characteristics of the compressor in the whole flow region.…”

Section: Introductionmentioning

confidence: 99%

A Computational Method of Rotating Stall and Surge Transients in Axial Compressor

et al. 2022

Energies

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The onset of rotating stall and surge in compressors limits the operating range of aero-engines. Accurately predicting the key features during these events is critical in the engine design process. In this paper, a three-dimensional computational model for transient simulation of multi-stage axial compressors during stall is proposed. The kinetic equations describing the dynamic process of the compression system are constructed, with a 3D through-flow model for the compression part and a 1D gas collector model for the outlet part. The calculation of the source term is performed using the developed body-force model, which realizes the correlation between the deviation angle and the loss coefficient with the inlet parameters in various flow regions. Validated on a single-stage compressor and a single-rotor fan, the results show that the method is capable of capturing the stall and surge features correctly and that the three-dimensional structure of the stall cell can be captured. In addition, this model could be used for the analysis of the surge load, which is significant for the structural integrity of the compressor.

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An approximation for fully stalled cascades

Cited by 13 publications

References 1 publication

Reduced order modelling of full-span rotating stall for the flow control simulation of axial compressors

Reduced order modelling of full-span rotating stall for the flow control simulation of axial compressors

Stage performance influence on dynamic simulation of gas turbine compressors

A Computational Method of Rotating Stall and Surge Transients in Axial Compressor

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