通气孔对动叶冷却结构流动和换热特性的影响

为深入研究某型燃气轮高温旋转动叶片内部先进的复合冷却结构,采用三维气热耦合数值计算方法,模拟该叶片外部高温流场、内部前后冷却腔内蛇形折流通道复合冷却结构的流动性能与换热特性,研究前腔蛇形折流冷却通道在采用局部通气孔改进设计的条件下对整个旋转叶片外表面冷却效果与内部冷却通道流阻系数的改善程度。计算结果表明:在给定的冷气流量条件下,无通气孔设计时,叶片内部蛇形折流通道采用的气膜/冲击/扰流复合冷却结构能够对叶片整体带来较好的换热效果,并且叶片内、外表面温度分布都处于合理范围,但由于整个内部折流冷却通道流动阻力较高,导致对冷却气源供应压力要求过大,且前后冷却腔室进口设计压力差别较大;在内冷前腔局部位置设计冷气通孔结构,可有效降低前腔折流通道的流动阻力,在保证叶片换热效果没有受到明显影响的前提下,实现了所需冷气供应压力和冷气量同时显著下降,多腔冷却气体用量得到更好匹配。该改型设计提高了原型叶片的工程应用价值。

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

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 blade.The reliability of these methods is verified by comparing experimental data.For 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 conducted.Based 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 distribution.Through 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 inlets.The results show that the proposed calculation methods can remarkably reduce the design cycle of complex turbine blade cooling structure.

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

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 states.The 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 forces.It 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 height.In addition,it increases the slope of the limiting streamline,which has a decisive influence on the heat transfer of both the pressure and suction surfaces.The paper provides guidance for the design of a rotating composite cooling structure based on the relations between the stationary and rotational conditions.

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

This paper presents a new idea to reduce the solidity of low-pressure turbine(LPT) blade cascades,while remain the structural integrity of LPT blade.Aerodynamic 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 efficiency.For 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 presented.The results show that appropriate TET is important for the optimal design of high-lift load LPT blade cascades.

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

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.

Flow Visualization and Topological Analysis of a Turbine Rotor Cascade with Tip Clearance

By means of ink trace visualization and topological allalysis, this paper investigates the topological structure of the flow pattern surrounding both endwalls and blade surfaces for a low aspect ratio linear rotor cascade with tip cIearance. The structure of the flow pattern shows that most of the singular points and separation lines are located in the upper half span region of the tested cascade where the aerodynamic behaviors are deteriorated.

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

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