Three-Dimensional Separated Flow Field in the Endwall Region of an Annular Compressor Cascade in the Presence of Rotor-Stator Interaction: Part 1—Quasi-Steady Flow Field and Comparison With Steady-State Data

Schulz, Henrik; Gallus, H. E.; Lakshminarayana, B.

doi:10.1115/1.2927707

Cited by 49 publications

(17 citation statements)

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“…However, the compressor blade loading is extremely limited by many 3-D flow losses in compressors, such as boundary layers, flow separations, leakages, and shocks. 1,2 During the last decades, the impact of corner separation in reducing the blade loading has been emphasized by many researchers, such as Dong et al, 3 Schulz et al, 4 Yocum and O'Brien, 5 Hah and Loellbach, 6 Gbadebo et al, 7 Lei, 8 Choi et al, 9 and Lewin et al 10 A corner separation forms at the junction between an end-wall (hub or casing) and a blade suction surface. It is closed off by limiting streamlines on walls, and a separation vortex is formed on the end-wall near the trailing edge, as sketched in Fig.…”

Section: Introductionmentioning

confidence: 99%

Large-eddy simulation of 3-D corner separation in a linear compressor cascade

Gao

Zambonini

et al. 2015

Physics of Fluids

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The increase of the thrust/weight ratio of aircraft engines is extremely restricted by different 3-D flow loss mechanisms. One of them is the corner separation that can form at the junction between a blade suction side and a hub or shroud. In this paper, in order to further investigate the turbulent characteristics of corner separation, large-eddy simulation (LES) is conducted on a compressor cascade configuration using NACA65 blade profiles (chord based Reynolds number: 3.82 × 10 5), in comparison with the previous obtained experimental data. Using the shear-improved Smagorinsky model as subgrid-scale model, the LES gives a good description of the mean aerodynamics of the corner separation, especially for the blade surface static pressure coefficient and the total pressure losses. The turbulent dynamics is then analyzed in detail, in consideration of the turbulent structures, the one-point velocity spectra, and the turbulence anisotropy. Within the recirculation region, the energy appears to concentrate around the largest turbulent eddies, with fairly isotropic characteristics. Concerning the dynamics, an aperiodic shedding of hairpin vortices seems to induce an unsteadiness of the separation envelope.

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Section: Introductionmentioning

confidence: 99%

Large-eddy simulation of 3-D corner separation in a linear compressor cascade

Gao

Zambonini

et al. 2015

Physics of Fluids

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“…(1977 ). Some important experimental details have been presented later on by Marshal and Sieverding (1976), Moore and Rahsmayr (1984), Moore and Smith (1984), Sonoda ( 1985 ), Goldstein and Spores (1988), Langston (1990), Chung and Simon (1990), Joslin and Dring (1992), Schultz et al (1990), Jabbari et a!. ( 1992 ).…”

Section: Introductionmentioning

confidence: 99%

Improved Approach to an Endwall Heat Transfer Analysis: A Linear Guide Vane and a Curved Duct

Халатов

1998

Volume 4: Heat Transfer; Electric Power; Industrial and Cogeneration

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This paper consists of two sections. The first section of the paper illustrates successful application of the improved approach developed by author to the endwall heat transfer data analysis in a low speed linear guide vane and in a curved duct. Effects of a three dimensional turbulent flow, a horseshoe vortex, a passage vortex, as well as an entry boundary layer thickness have been considered in both passages and as a result the common experimental correlation on a local heat transfer have been derived for the H/t = 1.0 ratio. All affected factors are presented as a superposition of the linear correction functions in the basic experimental correlation for a flat plate heat transfer. In the second section the common correlation is used as the reference correlation to establish effect of the span-to-pitch ratio on the endwall heat transfer in both passages. It was found that variation in the H/t ratio affects slightly the freestream velocity; the most important result which came from the heat transfer study is that in contrast to a curved duct a heat transfer rate in a blade passage is reduced while the H/t ratio decreases. Comparison of the experimental data obtained by the author with results of the two-dimensional heat transfer prediction confirms that it is very important to take a three-dimensional heat transfer nature into account in design of the endwall convective cooling system. It has been demonstrated that distinction between the results of two- and three dimensional approach to the endwall heat transfer can achieve up to 70% at the passage’s inlet area.

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“…Many researchers have contributed to this present state of knowledge and it would be hardly possible to list them all. Out of an arbitrary selection, containing also references to earlier work, we can refer to Langston et al (1977), Chen and Goldstein (1991), for turbine blade rows, to Schulz et al (1990), Cumpsty (1989), Kang and Hirsch (1994) for compressor blade rows.…”

Section: Introductionmentioning

confidence: 99%

A Numerically Supported Investigation of the 3D Flow in Centrifugal Impellers: Part I — The Validation Base

Hirsch

Kang

Pointel

1996

Volume 1: Turbomachinery

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The three-dimensional flow in centrifugal impellers is investigated on the basis of a detailed analysis of the results of numerical simulations. In order to gain confidence in this process, an in-depth validation is performed, based on computations of Krain’s centrifugal compressor and of a radial pump impeller, both with vaneless diffusers. Detailed comparisons with available experimental data provide high confidence in the numerical tools and results. The appearance of a high loss ‘wake’ region results from the transport of boundary layer material from the blade surfaces to the shroud region and its location depends on the balance between secondary and tip leakage flows and is not necessarily connected to 3D boundary layer separation. Although the low momentum spots near the shroud can interfere with 3D separated regions, the main outcome of the present analysis is that these are two distinct phenomena. Part I of this paper focuses on the validation base of the numerical approach, based on fine mesh simulations, while Part II presents an analysis of the different contributions to the secondary flows and attempts to estimate their effect on the overall flow pattern.

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Three-Dimensional Separated Flow Field in the Endwall Region of an Annular Compressor Cascade in the Presence of Rotor-Stator Interaction: Part 1—Quasi-Steady Flow Field and Comparison With Steady-State Data

Cited by 49 publications

References 0 publications

Large-eddy simulation of 3-D corner separation in a linear compressor cascade

Large-eddy simulation of 3-D corner separation in a linear compressor cascade

Improved Approach to an Endwall Heat Transfer Analysis: A Linear Guide Vane and a Curved Duct

A Numerically Supported Investigation of the 3D Flow in Centrifugal Impellers: Part I — The Validation Base

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