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Effect of cross-flow direction of coolant on film cooling effectiveness with one inlet and double outlet hole injection

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Propulsion and Power Research 2012年第1期1卷 71-77页

作者： Guangchao Lin Chaolin Wu Wei Zhang Zhihai Kou Dawei Peng Liaoning Key Laboratory of Advanced Technology for Aeronautical Propulsion System Aeroengine and Energy Engineering CollegeShenyang Aerospace UniversityShenyangLiaoning 110136China

In order to study the effect of cross-flow directions of an internal coolant on film cooling performance,the discharge coefficients and film cooling effectiveness with one inlet and double outlet hole injections were *** numerical results show that two different cross-flow directions of the coolant cause the same decrease in the discharge coefficients as that in the case of supplying coolant by a *** different proportion of the mass flow out of the two outlets of the film hole results in different values of the film cooling effectiveness for three different cases of coolant *** film cooling effectiveness is the highest for the case of supplying coolant by the *** a lower blowing ratio of 1.0,the film cooling effectiveness with coolant injection from the right entrance of the passage is higher than that from the left entrance of the *** a higher blowing ratio of 2.0,the opposite result is found.

关键词： Aerospace propulsion system Turbine blade film cooling Cross-flow Numerical simulation

Computational research on film cooling under rotating frame by an anisotropic turbulence model

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Propulsion and Power Research 2013年第1期2卷 20-29页

作者： Jianqin Zhu Kai Wang Chaoqun Nie National Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamics School of Energy and Power EngineeringBeihang UniversityBeijing 100191China Institute of Engineering Thermophysics Chinese Academy of SciencesBeijing 100190China

A new anisotropic k-o turbulence model was proposed in this *** new model,with the standard k-o model and the standard k-e model was embedded in our three-dimensional(3-D)Navier-Stokes code to compute rotational film *** addition,the theoretical and numerical analysis on the influence of the Coriolis and buoyancy forces induced by the rotation was discussed in *** findings of this study are as follows:⑴The new anisotropic k-o model preformed much better compared to its isotropic counterparts.(2)In the region of 6D-12D downstream the film hole,the numerical results of the new model were much closer to the experimental data than that in the region of 0-6D.(3)The constant density term can be balanced by the pressure gradient and would not influence the velocity and temperature *** the centrifugal buoyancy force and the Coriolis force would change the trajectory of cooling air and temperature distributions.

关键词： film cooling Turbulence model Rotation Coriolis force Centrifugal force

Numerical study on film cooling mechanism and characteristics of cylindrical holes with branched jet injections

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Propulsion and Power Research 2013年第1期2卷 30-37页

作者： Yu Yao Jingzhou Zhang Yang Yang School of Aircraft Engineering Nanchang Hangkong UniversityNanchang 330063China College of Energy and Power Engineering Nanjing University of Aeronautics and AstronauticsNanjing 2І00І6China

The film cooling mechanism and characteristics of a row of cylindrical holes with branched jet injections were investigated by numerical *** geometries for the branched jet injection holes and four blowing ratios were *** results led to the following conclusions:(1)when additional branched jet injections supplement the primary holes,the kidney vortices are suppressed,and film lateral coverage is enlarged,which improves the film cooling effectiveness;(2)suppression of kidney vortices from the primary holes is due to anti-vortex and coolant-distribution actions by the additional branched jet injections;(3)when the exit of the branched jet injection holes is located in line with the primary film cooling holes,a lower heat transfer coefficient ratio and higher film cooling effectiveness are achieved;(4)the film cooling effectiveness is clearly improved by additional branched jet injections under higher blowing ratios.

关键词： film cooling Branched jetinjection holes cooling effectiveness Heat transfer Numerical simulation

Investigation of film cooling on the leading edge of turbine blade based on detached eddy simulation

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Science China(Technological Sciences) 2012年第9期55卷 2191-2198页

作者： LIANG JunYu KANG Shun Key Laboratory of Condition Monitor and Control for Power Plant Equipment of Ministry of Education North China Electric Power UniversityBeijing 102206China

In order to assess the influences of curved hole passage on cooling effectiveness and flow structure of turbine blade leading edge,the detached eddy simulation is applied to numerically investigate the AGTB turbine cascade under the condition of global blowing ratio M=*** straight or curved cooling holes are located at either the pressure or suction side near the leading *** analysis and discussion focus on the local turbulence structure;influence of pressure gradient on the structure,and distribution of cooling effectiveness on the blade *** numerical results show that cooling hole with curved passage could bring positive impact on the increase of the local cooling *** the suction side,the increased cooling effectiveness could be about 82% and about 77% on the pressure side,compared to the conventional straight hole.

关键词： film cooling blade leading edge detached eddy simulation cooling effectiveness coherent structure

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EXPERIMENTAL STUDY ON film cooling EFFECTIVENESS AND HEAT TRANSFER COEFFICIENT BY NAPHTHALENE SUBLIMATION

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Chinese Journal of Aeronautics 1999年第3期12卷 16-21页

作者：杨汇涛曹玉璋朱谷君

Based on the linearity of the heat transfer coefficient and dimensionless temperature ratio, and analogy between heat and mass transfer, an experimental study on film cooling characteristic was carried out with a novel naphthalene sublimation. In general, cooling effectiveness distributions have been obtained on adiabatic surface, but separate testing on a non adiabatic wall is required to determine the heat transfer coefficient distribution. This novel naphthalene sublimation, which is different from previous heat transfer or analogy method, can measure both cooling effectiveness and heat transfer coefficient together with the same test section. The results show well by being compared with other references.

关键词： film cooling naphthalene sublimation analogy

Effect of Diffusively Shaped Holes on the Turbulent Flow Field of a film cooling Plate

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Chinese Journal of Aeronautics 2002年第1期15卷 6-11页

作者：施红辉桐山贤司伊藤基之 Department of Mechanics Zhejiang University Hangzhou 310027 China Department of Mechanical Engineering Nagoya Institute of Technology Nagoya 466-8555 Japan

The gas turbine blades with diffusion film cooling holes are newlydeveloped blade struc- tures in the hydrogen combustion gas turbine,which has an extremely high inlet gas temperature (1700 deg. C). TheFluid Machinery Laboratory of Nagoya Institute o Technology conductedfirstly a new research o the turbulent flow field over the gasturbine blade with diffusion film cooling holes in Japan. Normal-typeand X-ray hot wires were applied in the measurement of the flowfield.

关键词： turbulent boundary layer film cooling diffusion hole hot wireanemometry

Study of Turbulent Flow of film cooling Holes with Lateral Expanded Exits

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Chinese Journal of Aeronautics 2002年第4期15卷 200-207页

作者：施红辉佐佐俊祐 Department of Mechanics Zhejiang University Hangzhou 310027 China LNM Institute of Mechanics Chinese Academy of Sciences Beijing 100080 China Department of Mechanical Engineering Nagoya Institute of Technology Nagoya 466-8555 Japan

Hot wire measurements and flow visualization are presented for studying the turbulent flow field over a flat gas turbine film cooling blade with lateral expanded holes. Three mass flux ratios of jet to free stream, M = 0.5, 0.89, 1.5, are tested. The streamwise velocity, the turbulent intensities and the Reynolds shear stress are measured. The effect of the lateral expanded holes on the improvement of the turbulent flow field for film cooling of gas turbines can be analyzed from the measured spatial di...

关键词： turbulent flow film cooling lateral expanded hole hot wire anemometry flow visualization

Hybrid RANS-LES of Shaped Hole film cooling on an Adiabatic Flat Plate at Low Reynolds Number

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Open Journal of Fluid Dynamics 2020年第4期10卷 317-341页

作者： Michael Boehler Akshay Sudesh Mark Turner Department of Aerospace Engineering & Engineering Mechanics University of Cincinnati Cincinnati USA

Hybrid RANS-LES methods offer a means of reducing computational cost and setup time to simulate transitional flows. Several methods are evaluated in ANSYS CFX, including Scale-Adaptive Simulation (SAS), Shielded Detached Eddy Simulation (SDES), Stress-Blended Eddy Simulation (SBES), and Zonal Large Eddy Simulation (ZLES), along with a no-model laminar simulation. Each is used to simulate an adiabatic flat plate film cooling experiment of a shaped hole at low Reynolds number. Adiabatic effectiveness is calculated for Blowing Ratio (BR) = 1.5 and Density Ratio (DR) = 1.5. The ZLES method and laminar simulation most accurately match experimental lateral-average adiabatic effectiveness along the streamwise direction from the trailing edge of the hole to 35 hole diameters downstream of the hole (X/D = 0 to X/D = 35), with RMS deviations of 5.1% and 4.2%, and maximum deviations of 8% and 11%, respectively. The accuracy of these models is attributed to the resolution of turbulent structures in not only the mixing region but in the upstream boundary layer as well, where the other methods utilize RANS and do not switch to LES.

关键词： film cooling Large Eddy Simulation Detached-Eddy Simulation Stress-Blended Eddy Simulation Laidback Fan-Shaped cooling Hole film cooling Effectiveness

Numerical Analysis of Microholes film/Effusion cooling Effectiveness

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Journal of Thermal Science 2017年第5期26卷 459-464页

作者： Tomasz Ochrymiuk Institute of Fluid-Flow Machinery Polish Academy of Sciences (IMP PAN) Fiszera 14 80-952 Gdansk

Numerical simulations were performed to predict the film cooling effectiveness on the fiat plate with a three-dimensional discrete hole film cooling RSM-AKN turbulent heat transfer models based on variable turbulent Prandtl number approaches were considered. Obtained numerical results were directly compared with the data that came from an experiment based on Transient Liquid Crystal methodology. All implemented models for turbulent heat transfer performed sufficiently well for the considered case. It was confirmed, however, that the two-equation closure can give a detailed look into film cooling problems without using any time-consuming and inherently unsteady models. The RSM-AKN turbulent model was used in micoholes case too. The main target of simulations was maintain the same level of cooling efficiency ratio in both cases and confirm that is possible significantly reduce mass flows of the coolant in microholes case.

关键词： turbulent heat flux two-equation model turbulent Prandtl number film cooling microholes