Numerical Simulation of Rotating Stall in Axial Compressor Blade Rows and Stages

Neuhoff, Heinz G.; Grahl, Klaus

doi:10.1115/86-gt-27

Cited by 5 publications

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“…Equation ( 6) has a similar form to one obtained years ago without apparently making use of blade forces. 12 It holds both in the absolute frame and in that relative to the blade circumferential motion because, unlike original momentum equations, no longer contains the swirl velocity. This property suggests rewriting of the energy equation in the relative frame, where, by definition of inviscid and viscous forces, none of them works on the flow.…”

Section: Governing Flow Equationsmentioning

confidence: 99%

Time-marching solution of transonic flows at axial turbomachinery meanline

Taddei

2020

Proceedings of the Institution of Mechanical Engineers, Part G:

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A new blade force model is coupled to quasi-one dimensional Euler equations for a variable geometry flowpath. After analytical inclusion of the blade force, the flow equations take a strictly one-dimensional form with specific expressions of the convective flux and blade load source terms. Regardless of the flow turning, that is simply achieved by the load source term as an explicit function of the blade camber, the new form describes a perfect analogy between the average flow inside a blade passage and strictly one-dimensional flows, especially concerning wave propagation. This property allows capture of passage choking and shocks. Other types of shock more important for turbomachinery analysis, like leading edge strong shocks in compressors and trailing edge weak shocks in choked turbines, are modelled by properly matching the new set of equations inside blade regions with the standard quasi-one dimensional equations outside. Upon specification of viscous losses and subsonic deviations fitted from experimental results, the model predicts the choke mass flow of a transonic compressor stage (NASA stage 37) at a 0.1% to 0.4% accuracy both in the absence and in the presence of the leading edge shock. This result supports the effectiveness of the leading edge shock model. The accuracy on choke mass flow would decrease to around 1% if empirical input was specified from open-literature experimental correlations. The model captures the typical trend of exit angle with total pressure ratio for a choked turbine (NASA Lewis two-stage). This result involves satisfactory prediction of not only choke mass flow, but also trailing edge shock loss and supersonic deviation. The complete turbine operational map in terms of shaft torque and pressure ratio is also re-obtained with noticeable accuracy except in strong off-design conditions, where experimental correlations likely fail.

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Section: Governing Flow Equationsmentioning

confidence: 99%

Time-marching solution of transonic flows at axial turbomachinery meanline

Taddei

2020

Proceedings of the Institution of Mechanical Engineers, Part G:

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Rotierende Ablösung und Pumpen als gekoppelte Instabilitätsform in Axialverdichtern

Grahl

Foitzik²

1987

Forsch Ing-Wes

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Numerical simulation of flow instabilities in high speed multistage compressors

Peters²,

Fottner³

1999

J. of Therm. Sci.

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P o w e r E n g i n e e r i n g D e p a r t m e n t , N a n j i n g U n i v e r s i t y of A e r o n a u t i c s & A s t r o n a u t i c s , N a n j i n g 210016, C h i n a T h o m a s P e t e r s L e o n h a r d F o t t n e r I n s t i t u t e for J e t P r o p u l s i o n , M u n i c h A r m e d Forces University, D-85577 N e u b i b e r g , G e r m a n yIn the present paper, a nonlinear multi "actuator disk" model is proposed to analyze the dynamic behavior of flow instabilities, including rotating stall and surge, in high speed multistage axial compressors. The model describes the duct flow fields using two dimensional, compressible and unsteady Euler equations, and accounts for the influences of downstream plenum and throttle in the system as well. It replaces each blade row of multistage compressors with a disk. For numerical calculations, the time marching procedure, using MacCormack two steps scheme, is used. The main purpose of this paper is to predict the mechanism of two dimensional short wavelength rotating stall inception and the interaction between blade rows in high speed multistage compressors. It has been demonstrated that the model has the ability to predict those phenomena, and the results show that some system parameters have a strong effect on the stall features as well. Results for a five stage high speed compressor are analyzed in detail, and comparison with the experimental data demonstrates that the model and calculating results are reliable.K e y w o r d s :

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Numerical Simulation of Rotating Stall in Axial Compressor Blade Rows and Stages

Abstract: Rotating stall is simulated by a time step integration procedure of the Euler equations. The prescribed compressors consist of finite inlet and outlet ducts, blade rows of finite chord lengths and a throttle without impedance. Due to this compressor model the net

Cited by 5 publications

References 0 publications

Time-marching solution of transonic flows at axial turbomachinery meanline

Time-marching solution of transonic flows at axial turbomachinery meanline

Rotierende Ablösung und Pumpen als gekoppelte Instabilitätsform in Axialverdichtern

Numerical simulation of flow instabilities in high speed multistage compressors

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