Corner stall control in linear compressor cascade by blended blade and endwall technique based on large eddy simulation

Recently bimodal phenomenon in corner separation has been found by Ma et al. (Experiments in Fluids, 2013, doi:10.1007/s00348-013-1546-y). Through detailed and accurate experimental results of the velocity flow field in a linear compressor cascade, they discovered two aperiodic modes exist in the corner separation of the compressor cascade. This phenomenon reflects the flow in corner separation is high intermittent, and large-scale coherent structures corresponding to two modes exist in the flow field of corner separation. However the generation mechanism of the bimodal phenomenon in corner separation is still unclear and thus needs to be studied further. In order to obtain instantaneous flow field with different unsteadiness and thus to analyse the mechanisms of bimodal phenomenon in corner separation, in this paper detached-eddy simulation (DES) is used to simulate the flow field in the linear compressor cascade where bimodal phenomenon has been found in previous experiment. DES in this paper successfully captures the bimodal phenomenon in the linear compressor cascade found in experiment, including the locations of bimodal points and the development of bimodal points along a line that normal to the blade suction side. We infer that the bimodal phenomenon in the corner separation is induced by the strong interaction between the following two facts. The first is the unsteady upstream flow nearby the leading edge whose angle and magnitude fluctuate simultaneously and significantly. The second is the high unsteady separation in the corner region.

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Application of High-Resolution Large Eddy Simulation to Simplified Turbomachinery Flows

Volume 2C: Turbomachinery ◽

10.1115/gt2016-57299 ◽

2016 ◽

Cited By ~ 1

Author(s):

Susumu Teramoto ◽

Takuya Ouchi ◽

Hiroki Sanada ◽

Koji Okamoto

Keyword(s):

Boundary Layer ◽

High Resolution ◽

Turbulent Boundary Layer ◽

Large Eddy Simulation ◽

Reynolds Stress ◽

Sudden Expansion ◽

Compressor Cascade ◽

Rans Model ◽

Eddy Simulation ◽

Large Eddy

Fully resolved large eddy simulation (LES) is applied to two simple geometry flowfields with well-defined boundary conditions. The LES results are compared with simulations based on a Reynolds-averaged Navier-Stokes (RANS) model with turbulence, and pros and cons of using high-resolution LES for turbomachinery flows are discussed. One flow is a linear compressor cascade flow composed of the tip section of GE rotor B at Rec = 4 × 105 with a clearance, and the other is a Mach 1.76 supersonic turbulent boundary layer at Reδ = 5000 that laminerizes through a 12-degree expansion corner. The grids are prepared fine enough to resolve the turbulent boundary layer through a grid sensitivity study. The liner cascade result shows that all the turbulent shear layers and boundary layers including those in the small tip clearance are well resolved with 800 million grid points. The Reynolds stress derived from the LES results are compared directly with those predicted from the Spalart-Allmaras one-equation RANS turbulence model. The two results agreed qualitatively well except for the shear layer surrounding the tip leakage vortex, demonstrating that the RANS model performs well at least for flowfields near the design condition. From the simulation of the turbulent boundary layer experiencing sudden expansion, noticeable decreases of both Reynolds stress and local friction coefficient were observed, showing that the turbulent boundary layer has relaminarized through the sudden expansion. The boundary layer downstream of the expansion exhibits a nonequilibrium condition and was different from the laminar boundary layer.

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Large eddy simulation of a compressor cascade and the influence of spanwise domain

Proceedings of the Institution of Mechanical Engineers Part A Journal of Power and Energy ◽

10.1177/0957650911409318 ◽

2011 ◽

Vol 225 (6) ◽

pp. 817-831 ◽

Cited By ~ 2

Author(s):

W A McMullan ◽

G J Page

Keyword(s):

Large Eddy Simulation ◽

Compressor Cascade ◽

Eddy Simulation ◽

Large Eddy

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Adaptive Detached Eddy Simulation of End-Wall Flow in a Linear Compressor Cascade

Volume 2C: Turbomachinery ◽

10.1115/gt2020-14526 ◽

2020 ◽

Author(s):

Zifei Yin

Keyword(s):

Pressure Coefficient ◽

Detached Eddy Simulation ◽

Compressor Cascade ◽

Local Flow ◽

Linear Compressor ◽

Eddy Simulation ◽

Wall Flow ◽

Linear Compressor Cascade ◽

End Wall ◽

Des Model

Abstract Delayed detached eddy simulations and wall-modeled eddy simulations using the adaptive DES model were performed to simulate corner separation in the Ecole Centrale de Lyon linear compressor cascade. The adaptive DES model directly uses length scale to define eddy viscosity, which makes it nature to compute the model constant CDES dynamically. The dynamic procedure adapts viscosity to local flow and grid. Delayed detached eddy simulations, with and without the dynamic procedure, were performed to demonstrate the benefit of adapting viscosity to local flow. Recycling method was adopted to generate inflow unsteady turbulent boundary layer for wall-modeled eddy simulations. The wall-modeled eddy simulation showed improvement over delayed-DES, in terms of static pressure coefficient around the blade and total pressure loss at downstream locations.

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Simulation of a compressor cascade with stalled flow using Large Eddy Simulation with two-layer approximate boundary conditions

Nuclear Engineering and Design ◽

10.1016/j.nucengdes.2008.07.015 ◽

2010 ◽

Vol 240 (2) ◽

pp. 321-335 ◽

Cited By ~ 5

Author(s):

N. Tauveron

Keyword(s):

Large Eddy Simulation ◽

Boundary Conditions ◽

Compressor Cascade ◽

Eddy Simulation ◽

Large Eddy ◽

Approximate Boundary Conditions

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Large Eddy Simulation of Pulsed Blowing in a Supersonic Compressor Cascade

Journal of Applied Fluid Mechanics ◽

10.29252/jafm.13.02.30272 ◽

2020 ◽

Vol 13 (2) ◽

pp. 479-490

Author(s):

Q. Meng ◽

S. Chen ◽

S. Ding ◽

H. Liu ◽

S. Wang ◽

...

Keyword(s):

Large Eddy Simulation ◽

Compressor Cascade ◽

Eddy Simulation ◽

Large Eddy

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Detached Eddy Simulation of Transition in Turbomachinery: Linear Compressor Cascade

Journal of Turbomachinery ◽

10.1115/1.4052309 ◽

2021 ◽

pp. 1-10

Author(s):

Zifei Yin ◽

Paul Durbin

Keyword(s):

Boundary Layer ◽

Large Scale ◽

Separated Flow ◽

Adaptive Model ◽

Detached Eddy Simulation ◽

Compressor Cascade ◽

Linear Compressor ◽

Eddy Simulation ◽

Delayed Detached Eddy Simulation ◽

Linear Compressor Cascade

Abstract The adaptive, l2-omega delayed detached eddy simulation model was selected to simulate the flow in the V103 linear compressor cascade. The Reynolds number based on axial chord length is 138,500. Varies inflow turbulent intensities from 0% to 10% were tested to evaluate the performance of the adaptive model. The adaptive model is capable of capturing the laminar boundary layer and the large scale perturbations inside it. The instability of large scale disturbances signals the switch to a hybrid simulation of turbulent boundary layer -- the transition front is thus predicted. In the case of separation-induced transition, the adaptive model, which uses eddy simulation in separated flow, can predict the separation bubble size accurately. Generally, the adaptive, delayed detached eddy simulation model can simulate the transitional separated flow in a linear compressor cascade, with a correct response to varying turbulent intensities.

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