舰船燃气轮机高压涡轮动叶多维热耦合设计方法

针对舰船燃气轮机复杂高效冷却叶片设计,基于压力修正算法建立冷却叶片一维管网设计方法;通过快速求解可压缩边界层微分方程获得叶片外换热边界,基于参数化的叶片网格生成方法,采用全隐式有限体积的固体导热求解方法,构建了冷却叶片的耦合传热模型,开发了耦合传热计算程序。对某高压涡轮动叶进行多维热耦合设计,确定冷却流路及冷气分布,通过三维气热耦合计算验证了设计方案的可行性,通过对比分析验证了多维热耦合设计方法对主要流通单元的流量、压力误差小于5%,具备较高的工程应用价值。     

燃气轮机高温叶片内部冷却技术概述

综述了燃气轮机典型的内部冷却结构和设计手段.通过文献分析,提出内部冷却典型强化换热手段包括带肋通道冷却、扰流柱冷却和冲击冷却,重要设计手段包括一维管网和三维数值优化.管网计算基于实验总结的经验公式,计算效率高,关键在于动量方程的求解算法;三维数值优化可以降低设计对人工经验的依赖,关键在于合理选择优化目标和优化算法.分析表明,旋流等新的强化传热形式、微型冷却等新的叶片冷却模式、旋转和真实通道几何对内部冷却详细传热和流场的影响都将得到进一步研究,叶片设计技术将由人工经验性的设计逐渐向计算机自动化方向发展.     

气膜冷却平板通道的数值模拟

对无肋和带45°肋气膜冷却平板通道的三维对流换热与导热耦合传热问题进行了数值模拟。网格划分采用非结构化网格,湍流模型为SSTk-ω模型,近壁处采用壁面函数法,采用SIMPLEC算法求解速度和压力的耦合。计算获得了无肋和带45°肋气膜冷却平板的流场分布和平板内外表面的平均温度和平均换热系数。计算结果表明,带45°肋的气膜冷却平板表面平均温度较无肋气膜冷却平板表面平均温度低,而近气膜孔区域冷、热表面平均换热系数较无肋时高,而且肋的存在对增大冷空气出流比有利。     

蜂窝内冷通道布局对叶片冷却效率的影响研究

为提高涡轮叶片耐温能力,将蜂窝冷却通道应用于涡轮叶片内部,通过流热耦合计算研究蜂窝冷却通道叶片的传热流动特性。对蜂窝冷却通道的参数化方法进行研究,将蜂窝通道拆分成两种基本结构单元,即可方便调整蜂窝通道的几何参数;使用增材制造的叶片进行实验,通过对比数值计算与实验的冷却效率,验证了数值方法的准确性;在冷却二次流占比1%条件下,在原型蜂窝通道的基础上进行蜂窝通道空间布局和直径分布的调整,利用冷却效率、压降及相对阻力系数衡量不同通道的流动传热特性。研究表明：蜂窝通道由于增大换热面积以及增加分叉点强化换热,冷却效率提高到0.525,压降升高至229.1 kPa;通过调整蜂窝几何参数可以优化蜂窝通道的传热与阻力特性,通过增加蜂窝通道层数、增大次通道直径可以提高冷却效率,通过增加蜂窝通道入口数、增大主通道直径可以减小压降。     

超声速燃烧室再生冷却结构对传热的影响分析

采用有限容积法结合对流换热关联式与蒙特卡罗法,建立了超声速燃烧室再生冷却通道的耦合换热计算模型。冷却燃料为煤油,其密度、导热系数、动力粘度随温度和压力变化,煤油比热容与金属结构的热物性随温度变化。在考虑再生冷却面板尺寸与冷却燃料量保持不变的耦合性限制条件下,计算分析了非均匀热流密度下,冷却通道内壁厚度、高度、宽度及侧肋厚度对冷却性能的影响。研究结果表明,通道结构参数的变化引起结构传热热阻和冷却剂对流换热性能以及总换热面积、通道个数的变化,在传热分析中应综合考虑。     

某重型燃机透平动叶冷却结构设计

在对某重型中低热值燃机透平动叶冷却结构分析的基础上,采用流体计算软件建立气热耦合计算模型,完成叶片内外部流场和温度场气热耦合计算,并对冷却结构的换热效果进行分析,在不增大冷却流量的前提下增加湍流结构提高了叶片的冷却效果。     

大功率汽轮机叶轮轮缘传热系数的研究

提出了大功率汽轮机叶轮轮缘总传热系数的计算方法.介绍了汽轮机动叶片叶身平均对流换热表面传热系数和叶片流道下壁面对流换热表面传热系数的计算方法和计算公式.把汽轮机叶片对叶轮的传热简化为肋片传热,使用肋片传热模型计算汽轮机叶片流道的等效传热系数,采用圆筒壁模型计算汽轮机叶轮轮缘的总传热系数,并给出了应用实例.在汽轮机转子的温度场与热应力场有限元分析中,该计算方法为确定叶轮轮缘的传热边界条件提供了依据.     

具有新型双层壁结构的透平叶片流热耦合研究

多通道壁面射流冷却结构是一种新型的燃气透平动叶内部冷却结构,具有消耗冷气少、压力损失小等优点。本文构建了简化的壁面射流冷却叶片与GE-E3冷却结构叶片模型,采用流热耦合方法对比研究了其流动与换热特性。结果表明,壁面射流冷却通道内的狭小空间抑制了横流的产生,冷气在冷却通道中形成了流向涡;前缘冷气流道中的大量冷气流经吸力侧冷却区,并从出口压力更小、面积更大的尾缘排出,使得前缘气膜孔出流的冷气流量和动量较小,冷气在叶片外表面的气膜覆盖特性更好;离心力的影响导致前缘冷气流道中叶根处的压力较低,叶根附近的气膜孔出现燃气主流入侵现象。相比于GE-E3叶片,壁面射流冷却叶片的前缘温度和温度梯度都较小,因此多通道壁面射流冷却在前缘具有更优异的冷却特性。     

基于响应面的涡轮交叉肋气动和传热特性研究

提高涡轮进口温度是有效提升燃机热效率的重要途径,交叉肋冷却结构因其冷却效率高、冷却气体用量少的特点受到广泛关注。本文按照采用响应面设计方法得到的曲面优化设计方案,对某型涡轮叶片局部交叉肋冷却结构流道进行数值模拟,分析了肋宽与肋间距以及肋片倾斜角度对交叉肋通道换热与流阻特性的影响,结果表明：肋倾角小,肋宽与肋间距之比大,雷诺数小的方案换热能力更强,雷诺数高的方案的阻力损失更大;肋倾角大,肋宽与肋间距之比小,雷诺数小的方案综合换热效果更好。此外,结合响应面方法获得了该局部位置交叉肋的气动和传热性能的预测公式。三组回归预测方程的预测值与数值模拟值的平均误差分别为3.7%、6.5%、4.6%,一定程度上为后续交叉肋结构的优化设计奠定了基础。     

双层壁叶片的模型化方法与冷却设计流程研究

提出了一种适用于双层壁叶片的冷却设计流程。沿叶片的叶高和流向抽象提取出简单冷却单元,对其建立一维管网模型并进行多次管网计算,得出各个单元最优的冷却结构方案。将设计好的冷却单元映射回实际叶片中,并对叶片建立一维管网模型,经过多次冷却结构调整与计算迭代,得到叶片初步的冷却结构。对该叶片进行三维气热耦合计算,只需要局部冷却结构微调和少量的CFD计算,就可以得出最终的冷却设计方案。最终设计的叶片CFD计算得到的平均温度为1 049 K,总冷气量为0.288 kg/s,与管网计算结果1 059 K和0.337 kg/s相近。该设计流程方法简便,准确性高,人工工作量和仿真计算量小,优于传统的涡轮冷却设计流程。     

燃气轮机叶片内部直通道的肋片结构优化

提出了一种新型燃机透平叶片带肋直通道结构优化策略,采用ANSYS Workbench优化设计平台,应用Kriging代理模型和遗传算法对燃机叶片内宽高比为4、肋片角度为45°的带肋直通道进行了优化计算。结果表明:在带肋直通道切除部分肋片效率为负的肋片的新型结构可实现强化换热且降低流阻;优化后的肋片通道较未优化的通道,换热性能因子提升2. 9%,摩擦因子比降低可达3. 8%;通过寻优计算,获得了宽高比为4,肋片倾斜角度45°燃机叶片内带肋直通道最优结构参数。     

燃气轮机叶片内部扰流肋冷却方式研究进展

随着燃气透平转子进口温度的不断提高,燃气轮机叶片冷却日益重要。带有扰流肋的内部通道冷却是叶片冷却的一个重要部分。综述了内部扰流肋冷却的研究历程与研究现状,详细论述了静止状态下带肋内部通道的换热研究、旋转对带肋通道内换热的影响研究以及扰流肋与其他方式相结合的复合冷却研究。结论指出,在国内外静止状态下带肋通道内的换热研究已经很成熟,旋转对通道内流动与换热的影响是最近几年来的研究热点,而关于旋转状态下复合冷却方式的研究相对较少。优化旋转状态下内部肋结构和将内部扰流肋与其他冷却方式相结合的研究是今后的发展方向。     

基于流热耦合的燃气轮机透平叶顶冷却设计

燃气轮机透平叶顶区域存在复杂的流动和换热问题,承受很高的热负荷。为了降低透平动叶叶顶温度,在透平叶顶现有结构的基础上提出气膜冷却和气膜+内冷通道冷却两种叶顶冷却方案,并通过流热耦合计算分析冷却升级前后叶顶区域的换热和流动特性。研究发现：叶顶气膜冷却方案可有效降低叶顶温度,特别是叶顶前缘至中弦区域;而气膜＋内冷通道冷却方案基于外部气膜冷却,结合内部冷却通道设计,可进一步降低叶顶尾缘的温度;与原型叶片相比,气膜+内部冷气通道的复合冷却设计可以使叶顶尾缘最高温度降低24 K。     

Numerical Optimization of Turbulent Flow and Heat Transfer Characteristics in a Ribbed Channel

By using an optimal method coupled with the numerical simulation of the response surface methodology and genetic algorithm, the geometric configuration for two-dimensional ribbed channels is optimized in this paper. The parameters studied are the height of rib, the thickness of rib, and the pitch. The objective of optimization is to maximize the performance factor of the ribbed channel. The results show that the optimal method works for an optimized design of a two-dimensional ribbed channels. The ribs are demonstrated such that they can significantly affect the heat transfer rate and the friction factor. For the in-line ribbed channel, the performance factor increased by 1.1–1.5. In a staggered ribbed channel, the performance factor reached 2.681.     

Large eddy simulation of flow and heat transfer in a rotating ribbed channel

The internal cooling passage of a gas turbine blade equipped with ribs is modeled as a rotating ribbed channel. The flow and heat transfer in the ribbed channel have been investigated by conducting large eddy simulations with a dynamic subgrid-scale model. The Reynolds number considered is 30,000 and rotation numbers are 0, 0.1 and 0.3. The time-averaged results show good agreement with the experimental data. By comparing the present data with those of the smooth channel, it is observed that the vortices shed from the rib induce strong wall-normal motions, and they are augmented on the trailing-wall side by the rotation, resulting in a significant increase in the heat transfer due to rotation. It is also shown that the similarity between the streamwise velocity and temperature is significantly destroyed by both the rotation and the rib itself.     

涡轮叶片尾缘扰流柱最佳形状的研究

以涡轮叶片尾缘中扰流柱的换热为应用背景，讨论了一定条件下获得最大换热量时扰流柱的形状曲线，系统分析了这种最佳曲线随扰流柱物性参数及几何特征变化的规律。     

Design criteria for ribbed channels: Experimental investigation and theoretical analysis

The present study investigates heat transfer and pressure drop in flows through ribbed channel for application to turbine blade cooling. The experiments are conducted for different cross-sections, for Reynolds number from 20 to 60 × 10³. Local heat transfer coefficients are obtained using a transient thermochromic liquid crystal (TLC) technique. Detailed knowledge of the local heat transfer coefficient is essential to analyze thermal stresses in turbine components, while the combined effect of heat transfer and pressure drop should be taken into account for a proper cooling system design. As a compromise has always to be found, a new design criteria to choose the most appropriate solution for typical turbomachinery parameters is inferred and shown. Entrance effects for ribbed channels are also studied, as the common hypothesis of fully developed flow is rarely satisfied in real engine geometries; relevant results are revealed.     

A numerical framework for heat transfer and pressure loss estimation of matrix cooling geometry in stationary and rotational states

This study conducts an investigation and feasibility study on different Reynolds numbers (6000–12000) and Rotation numbers (0.05–0.25) in a matrix cooling geometry. An intended geometry that can be used in gas turbine blades is provided based on flow and heat transfer performance given in these Reynolds and rotation number ranges for stationary and rotational state and then compared with experimental data. In this work, a 3D simulation method for each states (stationary and rotation) has been used for two layers matrix cooling with four inlets in each layer in a straight rectangular channel. The results indicate that among the common methods used in the trailing edge of a gas turbine blade, the matrix cooling method has heat transfer in stationary and rotary states ～2–3 times higher than those of a smooth channel. Also results showed that rotation significantly affects heat transfer characteristics. Heat transfer increases in the pressure-side by a factor of 3 (at a Rotation number of 0.15 and Reynolds number 6000) which is an important property of rotation. According to the specific rotation direction chosen in this study, in comparison with previous studies, the pressure side and suction side location in stationary and rotation states are different and this results in lower decrease of heat transfer in the suction side for the rotation state. It is observed that using this structure increases the thermal performance about 30% by changing the flow behavior between stationary and rotary states.     

A Possible Strategy for the Performance Enhancement of Turbine Blade Internal Cooling With Inclined Ribs

Ribbing the internal passages of turbine blades with 45 deg inclined ribs is a common practice to achieve a good compromise between high heat transfer coefficients and not too large pressure drop penalties. Literature studies demonstrated that, for channels having a large aspect ratio, the effect of the secondary vortices induced by angled ribs is reduced and the heat transfer performance is degraded. In order to enhance the performance, a possible strategy consists in introducing one or more longitudinal ribs (intersecting ribs) aligned to the main direction of flow. The intersecting ribs cut the ribbed channel into separate sub-channels and markedly affect the secondary flows with consequent increases in heat transfer performance. Experiments were performed for a rectangular channel with a large aspect ratio (equal to five) and 45 deg inclined ribs, regularly spaced on one of the principal walls of the channel. The effect of one and two intersecting ribs on friction and heat transfer characteristics has been investigated. The ribbed surface of the channel has been electrically heated to provide a uniform heat flux condition over each inter-rib region. The convective fluid was air. Heat transfer experiments have been conducted by using the liquid crystal thermography. Results obtained for the ribbed channel without intersecting rib and with one/two intersecting ribs are compared in terms of dimensionless groups.