Quantification and Analysis of the Irreversible Flow Loss in a Linear Compressor Cascade

Li, Zhiyuan; Du, Juan; Ottavy, Xavier; Zhang, Hongwu

doi:10.3390/e20070486

Cited by 9 publications

(4 citation statements)

References 27 publications

(30 reference statements)

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“…The numerical analysis has been a good addition to the experimental research, and the computational fluid dynamics (CFD) is also an efficient approach [17][18][19]. Yu et al [20] applied the 13-component and 20-step reaction mechanism to investigate an oxygen/methane engine, and the results are consistent with experimental data.…”

Section: Introductionmentioning

confidence: 82%

Numerical Study on Combustion and Atomization Characteristics of Coaxial Injectors for LOX/Methane Engine

Jin

et al. 2021

International Journal of Aerospace Engineering

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The LOX/methane engine has an admirable performance under a supercritical state. However, the properties of methane change drastically with varying injection temperature. Because the injector can greatly affect the atomization and combustion, this study performed a three-dimensional numerical simulation of atomization, combustion, and heat transfer in a subscale LOX/methane engine to evaluate the effect of the main fluid parameters with different methane injection temperatures and different injectors on atomization performance and combustion performance. The results show that the larger propellant momentum ratio and Weber number can improve the heat flux and combustion stability in shear coaxial injector, while the influence in swirl coaxial injector is relatively small. Moreover, in shear coaxial injector and in swirl coaxial injector, the larger propellant momentum ratio and Weber number can reduce the droplet size, enhance atomization performance, and improve the combustion efficiency. The numerical model provides an economical method to evaluate the main fluid parameters and proposes new design principles of injectors in LOX/methane engine.

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Section: Introductionmentioning

confidence: 82%

Numerical Study on Combustion and Atomization Characteristics of Coaxial Injectors for LOX/Methane Engine

Jin

et al. 2021

International Journal of Aerospace Engineering

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“…(a)Original case (b)SJ case Figure 7 Time-averaged limiting streamline of suction side To evaluate the local irreversible loss of flow field, the entropy generation rate due to viscous shear inside the viscous sublayer at the inlet was used to normalize the entropy generation rate over the entire flow fields [10] . The irreversible loss are divided into four parts: the wake-flow region loss, the endwall boundary layer loss, the blade profile loss and the bladepassage loss.…”

Section: Te Le Te Lementioning

confidence: 99%

Numerical investigation on corner separation control in a linear compressor cascade by synthetic jet

Liu¹,

Wang²,

Huang³

et al. 2020

Proceedings of Global Power &Amp; Propulsion Society

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Corner separation is a kind of three-dimensional separation which occurs commonly in the junction of the endwall and blade corner region of high-loaded compressor. The increases of flow losses and the blockage associated with the corner separation have negative effect on the efficiency and stability of compressor. In this paper the flow control of corner separation by a synthetic jet is numerically investigated with the Reynolds Averaged Navier-Stokes/Large Eddy Simulation (RANS/LES) hybrid method to improve the cascade performance under the design condition. The synthetic jet is mounted on the blade suction side of a subsonic linear compressor cascade using NACA65 blade profiles. The influence of the synthetic jet on the vortex structures and unsteady characteristics in the cascade is investigated. The results indicate that, with the presence of synthetic jet, the passage vortex is weakened, and the corner vortex is receded indirectly. The intensity and range of the concentrated shedding vortex of the suction surface boundary layer are reduced. The total pressure loss coefficient is decreased by 25.8% at the design operating condition. Through calculating the entropy generation rate in the cascade, it is found that the blade profile loss is responsible for the additional flow losses. The synthetic jet significantly reduces the irreversible losses in the blade passage and wake region. From the perspective of the bimodal distributions of corner separation, the parameters increase first and then decrease, and the bimodal points appear in the abrupt velocity zone rather than at the separation points only.

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“…26 In order to further quantitatively evaluate the aerodynamic loss with inlet distortion, a new method inspired by Li et al. 27 was adopted here to calculate the entropy generation rate within the fan passage flows, which is a straightforward approach to quantify the irreversible flow losses. The entropy generation per unit volume is defined as follows where S·g″' represents the local entropy generation rate per volume, S·thermal ″' means the local entropy generation rate due to the heat transfer, S·visc″' means the local entropy generation rate due to the viscosity loss, κ is the thermal conductivity, T means the local temperature of fluid, μ is the air dynamic viscosity, and sij represents the shear strain rate.…”

Section: Flow Details With Inlet Stagnation Distortionmentioning

confidence: 99%

A study of fan-distortion interaction within the fan rotor

Zhang

et al. 2020

Proceedings of the Institution of Mechanical Engineers, Part A:

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Boundary-layer-ingesting fans and compressors in the next-generation turbofan engines require high-performance operations under distorted inflow. The aim of this work is to study the effects of inlet distortions including inlet stagnation pressure and temperature distortion, on the aerodynamic performance of a transonic axial fan. Firstly, the validated full-annulus, unsteady, three-dimensional computational fluid dynamic code in conjunction with detached Eddy simulation approach is used here to simulate the fan flows assembly with individual inlet stagnation pressure/temperature distortion. Then, the propagation process of the inlet distortion waves is analyzed to understand how the aerodynamic performance degradation is triggered. The simulation results show that the fan performance is remarkably degraded when the inlet distortion is introduced. The leading-edge spillage, the trailing edge back flow and the “tornado vortex” occur when parts of fan blades encounter the incoming distorted flows. Finally, the responses of fan to the combined inlet stagnation distortion effects are discussed in this paper. It is found that the combined distortion effects can be predicted based on the sum of the performance responses to the individual constituent distortions. Furthermore, the relative location of the constituent distortions shows a non-ignorable influence on the overall fan performance, especially for the intensified inlet distortion.

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Quantification and Analysis of the Irreversible Flow Loss in a Linear Compressor Cascade

Cited by 9 publications

References 27 publications

Numerical Study on Combustion and Atomization Characteristics of Coaxial Injectors for LOX/Methane Engine

Numerical Study on Combustion and Atomization Characteristics of Coaxial Injectors for LOX/Methane Engine

Numerical investigation on corner separation control in a linear compressor cascade by synthetic jet

A study of fan-distortion interaction within the fan rotor

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