Comparison of Theoretical and Semi-Empirical Solutions for Dissipation Coefficient in a Low Reynolds Number Compressor Cascade

This paper focuses on the compressor cascade experiment and numerical simulation at order 105 Reynolds number. A cascade tunnel simulated low Reynolds number condition under high subsonic speed. In a series of experiments (Re = 0.9 × 105∼5.0 × 105), oil flow visualization tests were used to indicate boundary layer development of the cascade surface. The results show that the performance of cascades deteriorates rapidly when the Reynolds number decreases to a certain extent. Comparison of results between the tests and calculations demonstrates that the real cascade experimental environment must be considered, such as the effect of the end wall. Flow separation and transition can be predicted accurately by using SST turbulence and Gamma transition models. Through modifying parameters of the Gamma transition model, the profile Mach number distribution in numerical simulations exhibits good agreement with experiments. Response surface methodology was adopted for the design process to minimize the total pressure loss of cascades at the design point. In addition, the optimized result has little negative effect on the high Reynolds number region.

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The Effect of Low Reynolds Number on Straight Compressor Cascades

Volume 5: Manufacturing Materials and Metallurgy; Ceramics; Structures and Dynamics; Controls, Diagnostics and Instrumentation; General ◽

10.1115/90-gt-221 ◽

1990 ◽

Cited By ~ 1

Author(s):

Jan Citavy ◽

Jaromir Jilek

Keyword(s):

Reynolds Number ◽

Low Reynolds Number ◽

Aerodynamic Performance ◽

Surface Flow ◽

Flow Visualisation ◽

Blade Surface ◽

Compressor Cascade ◽

Deviation Angle ◽

3D Effects ◽

Low Reynolds

New low-speed experimental results are presented concerning the effect of very low Reynolds number on the aerodynamic performance of a straight compressor cascade having 65 - 12 10 profile. The effect of Reynolds number on loss coefficient, deviation angle, pressure distribution and AVR within the range of Re = 104 − 105 is demonstrated including 3D effects. Blade surface flow visualisation has also been obtained. The results are compared with previous ones, e. g. by Roberts and are used for constructing a new model of very low Re effect on incompressible flow in a straight compressor cascade.

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Effect of Solidity on the Generation of Entropy in a Low Reynolds Number Compressor Cascade

2013 Aviation Technology, Integration, and Operations Conference ◽

10.2514/6.2013-4416 ◽

2013 ◽

Author(s):

Shigeo Hayashibara ◽

Roy Y. Myose ◽

Foo Kok

Keyword(s):

Reynolds Number ◽

Low Reynolds Number ◽

Compressor Cascade ◽

Low Reynolds

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Numerical Calculations of the Turbulent Flow Through a Controlled Diffusion Compressor Cascade

Journal of Turbomachinery ◽

10.1115/1.2835650 ◽

1995 ◽

Vol 117 (2) ◽

pp. 223-230 ◽

Cited By ~ 1

Author(s):

Shin-Hyoung Kang ◽

Joon Sik Lee ◽

Myung-Ryul Choi ◽

Kyung-Yup Kim

Keyword(s):

Reynolds Number ◽

Control Volume ◽

Low Reynolds Number ◽

Turbulence Models ◽

Compressor Cascade ◽

Mean Velocity ◽

Flow Angle ◽

Controlled Diffusion ◽

Flow Through ◽

Low Reynolds

The viscous flow through a controlled diffusion (CD) compressor cascade was calculated and compared with the measured data for two different test conditions. A control volume method was used, which has been developed for a generalized nonorthogonal coordinate system. The discretized equations for the physical covariant velocity components were obtained by an algebraic manipulation of the discretized equations for the Cartesian velocity components. Low Reynolds number k–ε turbulence models were used to obtain the eddy viscosity. The numerical scheme using the low Reynolds number k–ε turbulence model reasonably predicted the general performance, i.e, mean outlet flow angle and loss coefficients. The development of the shear layer along the pressure and suction sides was well estimated, and the physical features found in the experiment were reasonably well confirmed in the simulation. However, the calculated profiles of mean velocity and turbulent kinetic energy in the near wake show considerable disagreement with the measured values.

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