Scale Effect on the Gaseous Flow Around a Micro-Scaled Gas Turbine Blade

ASME 4th International Conference on Nanochannels, Microchannels, and Minichannels, Parts A and B ◽

10.1115/icnmm2006-96162 ◽

2006 ◽

Author(s):

Toru Yamada ◽

Yutaka Asako

Keyword(s):

Experimental Data ◽

Gas Turbine ◽

Turbine Blade ◽

Scale Effect ◽

Two Dimensional ◽

Arbitrary Lagrangian Eulerian ◽

Gas Turbine Blade ◽

Gaseous Flow ◽

Gaseous Flows ◽

Energy Equations

Two-dimensional compressible momentum and energy equations are solved on gaseous flows around a micro-scaled gas turbine blade (GE-E3) whose axial chord ranges from 86.1μm to 86.1mm to obtain the scale effect. The numerical methodology is based on Arbitrary-Lagrangian-Eulerian (ALE) method. The flow is assumed to be ‘no heat conduction’ flow. The computations were performed for gaseous flow around a single blade with periodical conditions imposed along the boundaries in the pitch directions. The study is focused on the effect of the scale of the turbine blade on the performance. The predicted pressure distribution on both the pressure and suction sides of the conventional sized blade and both the inlet and outlet Mach numbers were compared with available experimental data to verify the code and the scale effect was discussed.

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Effect of Compressibility on Gaseous Flows in a Micro-Tube

Heat Transfer: Volume 1 ◽

10.1115/ht2003-47166 ◽

2003 ◽

Cited By ~ 2

Author(s):

Yutaka Asako ◽

Kenji Nakayama

Keyword(s):

Reynolds Number ◽

Mach Number ◽

Pressure Distribution ◽

Flow Characteristics ◽

Fused Silica ◽

Two Dimensional ◽

Arbitrary Lagrangian Eulerian ◽

Gaseous Flow ◽

Gaseous Flows ◽

Energy Equations

The product of friction factor and Reynolds number (f·Re) of gaseous flow in the quasi-fully developed region of a micro-tube was obtained experimentally and numerically. The tube cutting method was adopted to obtain the pressure distribution along the tube. The fused silica tubes whose nominal diameters were 100 and 150 μm, were used. Two-dimensional compressible momentum and energy equations were solved to obtain the flow characteristics in micro-tubes. The numerical methodology is based on the Arbitrary-Lagrangian-Eulerian (ALE) method. The both results agree well and it was found that (f·Re) is a function of Mach number.

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Scale Effect on Gaseous Flow around a Micro-Scaled Gas Turbine Blade

Heat Transfer Engineering ◽

10.1080/01457630701326357 ◽

2007 ◽

Vol 28 (8-9) ◽

pp. 696-703 ◽

Cited By ~ 1

Author(s):

Toru Yamada ◽

Yutaka Asako

Keyword(s):

Gas Turbine ◽

Turbine Blade ◽

Scale Effect ◽

Gas Turbine Blade ◽

Gaseous Flow

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Numerical Analysis of Two-Dimensional Compressible Viscous Flow in Turbomachinery Cascades Using an Improved k-ε Turbulence Model

Volume 1: Aircraft Engine; Marine; Turbomachinery; Microturbines and Small Turbomachinery ◽

10.1115/97-gt-417 ◽

1997 ◽

Author(s):

Debasish Biswas ◽

Hideo Iwasaki ◽

Masaru Ishizuka

Keyword(s):

Boundary Layer ◽

Reynolds Number ◽

Viscous Flow ◽

Gas Turbine ◽

Turbine Blade ◽

Turbulence Model ◽

Higher Order ◽

Tvd Scheme ◽

Two Dimensional ◽

Gas Turbine Blade

In the present work two-dimensional viscous flows through compressor and gas turbine blade cascades at low subsonic and transonic speed are analyzed by solving compressible N-S equations in the generalized co-ordinate system, so that sufficient number of grid points could be distributed in the boundary layer and wake regions. An efficient Implicit Approximate Factorization (IAF) finite difference scheme, originally developed by Beam-Warming, is used together with a higher order Total Variation Diminishing (TVD) scheme based on the MUSCL-type approach with the Roe’s approximate Rieman solver for shock capturing. In order to predict the boundary layer turbulence characteristics, shock boundary layer interaction, transition from laminar to turbulent flow, etc. with sufficient accuracy, an improved low Reynolds number k-ε turbulence model developed by the authors is used. In this k-ε model, the low Reynolds number damping factors are defined as a function of turbulence Reynolds number which is only a rather general indicator of the degree of turbulence activity at any location in the flow rather than a specific function of the location itself. Computations are carried out for different flow conditions of compressor and gas turbine blade cascades for which detailed and reliable information about shock location, shock losses, viscous losses, blade surface pressure distribution and overall performance are available. Comparison of computed results with the experimental data showed a very good agreement. The results demonstrated that the Navier-Stokes approach using the present k-ε turbulence model and higher order TVD scheme would lead to improved prediction of viscous flow phenomena in turbomachinery cascades.

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Effect of Viscosity on Gaseous Flow in a Micro-Nozzle

Heat Transfer, Volume 2 ◽

10.1115/imece2004-61036 ◽

2004 ◽

Author(s):

Shintaro Murakami ◽

Yutaka Asako

Keyword(s):

Heat Conduction ◽

Analytical Solutions ◽

Two Dimensional ◽

Arbitrary Lagrangian Eulerian ◽

Numerical Computations ◽

Gaseous Flow ◽

One Dimensional ◽

Micro Nozzle ◽

Wide Range ◽

Energy Equations

Two-dimensional compressible momentum and energy equations are solved numerically to obtain the effect of viscosity on gaseous flow in a micro converging-diverging nozzle. The numerical methodology is based on the Arbitrary-Lagrangian-Eulerian (ALE) method. The numerical computations were performed for a wide range of the diverging angle and throat height and for no-heat conduction flow. The results are compared with one-dimensional analytical solutions for flow in a conventional sized nozzle and the effects of the viscosity on gaseous flow in the micro-nozzle are discussed.

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