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Numerical Study of Effects of Mach number on Aerodynamic Performance of Large Enthalpy Drop Stationary Cascade

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Journal of Thermal science 2014年第3期23卷 223-232页

作者： SHI Yuwen yan peigang han wanjin school of energy science and engineering Harbin Institute of Technology

Based on the method to change blade loading type along blade height, that is, applying aft-loading at both end zones of cascade while applying fore-loading in the mid zone of cascade, HTC(harbin Turbine Company) designed a twisted and bowed stationary cascade with low aspect ratio and large enthalpy drop. To verify the aerodynamic performance of such cascade, firstly, low-speed wind tunnel tests were conducted to validate the calculation results of commercial software CFX, and then numerical simulations were made for the aerodynamic performance of the cascade at different Mach numbers. The simulation results show that the large enthalpy drop stationary cascade designed by HTC can offer good aerodynamic performance while keeping its high-load characteristics in the change range of outlet Mach number as stated in this paper.

关键词： large enthalpy drop turbine blade low aspect ratio fore-loading, aft-loading

Unsteady Numerical Simulation of Steam-Solid Two-Phase Flow in the Governing Stage of a Steam Turbine

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Journal of Thermal science 2009年第4期18卷 313-320页

作者： Yufeng Li peigang yan wanjin han school of energy science & engineering Harbin Institute of Technology Harbin Heilongjiang 150001 China harbin Turbine Company Limited Harbin Heilongjiang 150046 China

Solid particle erosion (SPE) in an ultra-supercritical steam turbine control stage with block configuration is investigatednumerically, based on the finite volume method and the fluid-particle coupling solver. We apply the particlediscrete phase model to model the solid particles flow, and use the Euler conservation equations to solve thecontinuous phase. The investigation is focused on the influence of the solid particle parameters (such as particlediameter, particle velocity and particle trajectory) on the erosion rate of the stator and rotor blade surface in unsteadycondition. The distributions of the highly eroded zone on the stator and rotor blade surfaces are shown anddiscussed in detail according to the mechanism of solid particle/blade wall interaction. We obtain that the erosionrate of the vane blade is sensitive to the fluctuation of the potential flow field, and the smaller particle has agreater impact on the erosion distribution of rotor blade. The erosion rate does not entirely depend on the diametersize of the solid particle.

关键词： steam turbine unsteady numerical simulation solid particle erosion blade

Effects of Hot Steam Injection from the Slot at the Trailing Edge on Turbine Nozzle Vane Flow Field

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Journal of Thermal science 2008年第4期17卷 298-304页

作者： Liang Xu peigang yan Hongyan Huang wanjin han school of energy science ＆ engineering Harbin Institute of Technology Harbin 150001

Moisture removal slot configurations with three different opening widths are in turn set at the trailing edges of a turbine hollow guide *** flow fields are analyzed by two-phase flow numerical simulation of solving the steady three dimensional Reynolds averaged Navier-Stokes equations on the basis of the real water vapor thermo-physical properties,and the blade temperature field is solved by the fluid-solid *** parame- ter is introduced as a measure to evaluate the economic cost of energy conversion *** results indicate that the bigger slot allow lower quality of hot steam in the case of the equivalent injected quantity,while it has a higher exergy effective efficiency of the mixing process in the cascade *** hot steam injecting at the trailing edges has an optimal injected mass flow rate for a relatively large slot,on this point the exergy effective efficiency is the maximum,namely the flow loss is the minimum.

关键词： wet steam stationary blade moisture removal slot exergy analysis

BEM/FDM Conjugate Heat Transfer Analysis of a Two-dimensional Air-cooled Turbine Blade Boundary Layer

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Journal of Thermal science 2008年第3期17卷 199-206页

作者： Wang Zhenfeng yan peigang Guo Zhaoyuan han wanjin school of energy science and engineering Harbin Institute of Technology Harbin 150001 China

A coupled boundary element method （BEM） and finite difference method （FDM） are applied to solve conjugate heat transfer problem of a two-dimensional air-cooled turbine blade boundary layer. A loosely coupled strategy is adopted, in which each set of field equations is solved to provide boundary conditions for the other. The Navier-Stokes equations are solved by HIT-NS code. In this code, the FDM is adopted and is used to resolve the convective heat transfer in the fluid region. The BEM code is used to resolve the conduction heat transfer in the solid region. An iterated convergence criterion is the continuity of temperature and heat flux at the fluid-solid interface. The numerical results from the BEM adopted in this paper are in good agreement with the results of analytical solution and the results of commercial code, such as Fluent 6.2. The BEM avoids the complicated mesh needed in other computation method and saves the computation time. The results prove that the BEM adopted in this paper can give the same precision in numerical results with less boundary points. Comparing the conjugate results with the numerical results of an adiabatic wall flow solution, it reveals a significant difference in the distribution of metal temperatures. The results from conjugate heat transfer analysis are more accurate and they are closer to realistic thermal environment of turbines.

关键词： Conjugate heat transfer Boundary elements Finite difference Air-cooled gas turbine.

Numerical Investigation of Influence of Rotor/Stator Interaction on Blade Boundary Layer Flow in a Low Speed Compressor

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Journal of Thermal science 2011年第1期20卷 39-46页

作者： Yao Hongwei yan peigang han wanjin school of energy science ＆ engineering Harbin Institute of Technology Harbin 150001 China

Numerical method was applied to the unsteady flow simulation at the mid span of a two-stage low speed compressor,and the blade boundary layer flow under rotor/stator interaction was *** the model of wake/boundary layer interaction provided in this paper,the simulated blade frictional force and the boundary layer turbulent kinetic energy,the influence of wake/potential flow interaction on the blade boundary layer flow was analyzed in *** results show that under the condition of rotor/stator interaction,the wake is able to induce the stator laminar boundary layer flow to develop into turbulent flow within a certain range of wake *** the stator suction boundary layer,an undisturbed region occurs behind the rotor wake,which extends the laminar flow range,and the wake with high turbulent intensity has the capability to control the boundary layer separation under adverse pressure gradient.

关键词： Unsteady interaction Boundary layer Transition Wake Compressor

Rotation Effect on Flow and Heat Transfer for High-Temperature Rotor Blade in a Heavy Gas Turbine

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Journal of Thermal science 2021年第2期30卷 707-715页

作者： DONG Aihua yan peigang QIAN Xiaoru han wanjin WANG Qingchao school of energy science and engineering Harbin Institute of TechnologyHarbin 150001China harbin Turbine Company Limited Harbin 150046China

In this paper,the composite inner cooling structures of the rotating blade in the first stage heavy gas turbine were modeled and simulated by coupling heat transfer (CHT).The flow characteristics and heat transfer performances were comparatively analyzed under two operations of the stationary and the rotational *** results show that the turbulence intensity,the flow resistance and the heat transfer level of the rotating coolant are significantly increased compared with the stationary state,which is considered to be obtained by the combined effects of the Coriolis force,the centrifugal force and their derived buoyancy *** is pointed out that the rotation leads to the non-uniform flow of film holes at the leading edge of the pressure surface along blade *** addition,it increases the slope of the limiting streamline,which has a decisive influence on the heat transfer of both the pressure and suction *** paper provides guidance for the design of a rotating composite cooling structure based on the relations between the stationary and rotational conditions.

关键词： heavy gas turbine composite cooling structure coupled heat transfer rotation effect simulation

Numerical Study of Combining Steady Vortex Generator Jets and Deflected Trailing Edge to Reduce the Blade Numbers of Low Pressure Turbine Stage

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Journal of Thermal science 2016年第6期25卷 511-517页

作者： Li Chao yan peigang Wang Xiangfeng han wanjin WANG Qingchao school of energy science and engineering Harbin Institute of Technology

A flow control system that combined steady Vortex Generator Jets and Deflected Trailing-edge(VGJs-DT) to decrease the low pressure turbine(LPT) blade numbers was *** effects of VGJs-DT on energy loss and flow of low solidity low pressure turbine(LSLPT) cascades were ***-DT was found to decrease the energy loss of LSLPT cascade and increase the flow turning ***-DT decreased the solidity by 12.5%without a significant increase in energy ***-DT was more effective than steady ***-DT decreased the energy loss and increased the flow angle of the LSLPT cascade with steady ***-DT can use 50%less mass flow than steady VGJs to inhibit the flow separation in the LSLPT *** deflected trailing edge enhanced the ability of steady VGJs to resist flow ***,VGJs-DT can be used to control flow separation in LPT cascade and reduce the blade numbers of low pressure turbine stage.

关键词： Vortex cascade turbine resist blade Turbine Numbers turbulence projection pitch

Numerical Study of Improving Aerodynamic Performance of Low Solidity LPT Cascade through Increasing Trailing Edge Thickness

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Journal of Thermal science 2016年第4期25卷 342-348页

作者： LI Chao yan peigang WANG Xiangfeng han wanjin WANG Qingchao school of energy science and engineering Harbin Institute of Technology

This paper presents a new idea to reduce the solidity of low-pressure turbine(LPT) blade cascades,while remain the structural integrity of LPT *** performance of a low solidity LPT cascade was improved by increasing blade trailing edge thickness(TET).The solidity of the LPT cascade blade can be reduced by about12.5% through increasing the TET of the blade without a significant drop in energy *** the low solidity LPT cascade,increasing the TET can decrease energy loss by 23.30% and increase the flow turning angle by1.86% for Reynolds number(Re) of 25,000 and freestream turbulence intensities(FSTT) of 2.35%.The flow control mechanism governing behavior around the trailing edge of an LPT cascade is also *** results show that appropriate TET is important for the optimal design of high-lift load LPT blade cascades.

关键词： Aircraft engine low pressure turbine trailing edge thickness profile loss flow control

Retrofit design of composite cooling structure of a turbine blade by fluid networks and conjugate heat transfer methods

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science china(Technological sciences) 2013年第12期56卷 3104-3114页

作者： yan peigang SHI Liang WANG XiangFeng han wanjin school of energy science and engineering Harbin Institute of Technology

This article discusses the development of the numerical methods of gas flow coupled with heat transfer,and introduces the fluid net-works method for rapid prediction of the performance of the composite cooling structures in turbine *** reliability of these methods is verified by comparing experimental *** a HPT rotor blade,a rapid prediction on the internal cooling structures is first made by using the fluid network analysis,then an assessment of aerodynamic and heat transfer characteristics is *** on the network analysis results,three ways to improve the design of the cooling structures are tested,i.e.,adjusting the cooling gas flow mass ratios for different inner cooling cavities,reducing the flow resistances of the channel turning structures,and improving the local internal cooling structure geometries with high temperature *** the verification of full three-dimensional gas/solid/coolant conjugate heat transfer calculation,we conclude that the modified design can make the overall temperature distribution more even by significantly reducing the highest temperature of the blade surface,and reasonably matching the parameters of different coolant *** results show that the proposed calculation methods can remarkably reduce the design cycle of complex turbine blade cooling structure.

关键词： numerical simulation turbine blades conjugate heat transfer composite cooling structure fluid networks

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