燃气轮机叶片气膜冷却研究进展

综述了近年来燃气轮机涡轮叶片气膜冷却技术的研究成果.介绍了气膜冷却的基本原理,总结了叶片端壁、顶部、前缘及尾缘区域气膜冷却的研究进展和气膜孔流量系数的研究状况,阐述了影响气膜冷却效果的各种因素及气膜冷却对气动损失的影响.最后指出将气膜冷却与其它涡轮叶片冷却技术相结合的复合冷却,应是未来涡轮叶片冷却技术的发展方向.     

航空发动机涡轮叶片气膜冷却孔设计与制备技术研究进展

随着先进航空发动机对涡轮前燃气温度需求不断提升,涡轮叶片高效冷却设计技术成为亟待解决的瓶颈技术,而气膜孔冷却是涡轮叶片高效冷却设计的核心技术。本文基于航空发动机涡轮叶片采用耐高温复合材料与高效气膜冷却结构相结合的技术发展背景,综述国内外相关研究工作的进展,从涡轮叶片气膜孔的冷却机理、气膜孔的空间几何结构设计技术、气膜孔表面完整性制备技术等方面,深入总结分析涡轮叶片气膜冷却设计与制备技术领域取得的研究成果,重点论述了各国异型气膜冷却孔的设计与制备技术,并提出我国在该技术上存在的差距及未来研究重点。     

基于快响应压敏漆和高温磷光热图的气膜冷却非定常实验测量技术综述

涡轮内部流动及冷却射流的湍流特性决定了气膜冷却具有强烈的非定常性,精确获取高时空分辨率的气膜冷却换热特性对揭示其内在机理尤为重要。本文针对气膜冷却的非定常测试需求,聚焦于气膜冷却中涉及的壁面气膜动态覆盖以及叶片表面温度测量,从测量原理、测试系统及实际应用方面依次介绍了两种气膜冷却非定常实验测量技术。基于快响应压敏漆能够测量涡轮叶片、叶身及端壁的非定常气膜冷却,进而利用高温磷光热图评估近发动机工况下高温叶片表面的动态温度分布。     

2023年《热能动力工程》索引

涡轮内部流动及冷却射流的湍流特性决定了气膜冷却具有强烈的非定常性，精确获取高时空分辨率的气膜冷却换热特性对揭示其内在机理尤为重要。本文针对气膜冷却的非定常测试需求，聚焦于气膜冷却中涉及的壁面气膜动态覆盖以及叶片表面温度测量，从测量原理、测试系统及实际应用方面依次介绍了两种气膜冷却非定常实验测量技术。基于快响应压敏漆能够测量涡轮叶片、叶身及端壁的非定常气膜冷却，进而利用高温磷光热图评估近发动机工况下高温叶片表面的动态温度分布。     

气动参数对气膜孔流量系数的影响

使用数值计算方法研究了压比、内流马赫数、外流马赫数、吹风比、速度比等气膜冷却设计中常见的气动参数对气膜孔流量系数的影响。基于数值计算结果,提出了一种气膜孔流量系数的计算关联式。与文献中试验数据的对比表明,该关联式精度较高,可以为涡轮叶片冷却设计提供参考。     

重型燃气轮机涡轮叶片冷却技术研究进展

综述了重型燃气轮机涡轮叶片内部冷却技术、气膜冷却技术、蒸汽冷却技术的研究进展。提出了叶片内部冷却技术将集中在更真实运行条件下的流动与传热研究。新型气膜孔的优化与应用仍然是叶片气膜冷却技术的重点,优化气膜冷却效果需要更深入探究复合冷却流动与传热机理。蒸汽冷却技术的实际应用还较少,其基础理论研究也还在进行中。最后指出未来燃气轮机冷却技术研究集中在对已有结构冷却潜能的深入挖掘和对新式冷却技术的进一步探索。     

旋转对涡轮叶片气膜冷却影响的数值模拟

采用数值模拟的方法对旋转涡轮叶片表面的气膜冷却效率进行了研究,同时对涡轮静叶栅和动叶片在不同的旋转速度下分别进行计算,分析不同转速、吹风比和冷却气流喷射角度对气膜冷却的影响.计算结果表明,旋转使压力面气膜冷却效率降低,转速越高,气膜冷却效率越低;在吸力面冷却孔下游附近区域,叶片旋转对气膜冷却效率的影响不大,但叶片旋转使离冷却孔较远处的吸力面冷却效率升高.同时,在旋转状态下,靠近叶顶区域的叶片表面气膜冷却效率升高.     

低稠度涡轮导向叶片端壁高效气膜冷却特性研究

采用低稠度涡轮导向叶片设计方案，可减少导向叶片的用量，减轻涡轮重量，降低发动机冷气用量及耗油率，但同时也带来导向叶片端壁冷却负荷增大等问题。依据低稠度涡轮导向叶片端壁的结构与流动换热特点，制定了槽缝和气膜孔共同冷却的方案。通过数值模拟和分析，重点研究了低稠度涡轮导向叶片端壁前缘气膜孔在不同方向角、孔数、孔径以及叶栅通道中气膜孔布置等条件下的流动及冷却特性。研究结果表明：对低稠度涡轮导向叶片端壁前缘气膜孔进行优化设计，可以有效克服导向叶片端壁前缘高强度马蹄涡对于气膜冷却效果的不良影响；在叶栅通道内合理设置气膜孔，可以改善通道内复杂涡旋对端壁气膜的卷吸作用，提高气膜冷却效果；当槽缝和气膜孔中的冷气流量比分别为3%和2%、气膜孔方向角为45°、气膜孔直径为1.25 mm、叶片前缘和叶栅通道气膜孔数分别为8和1时，叶片端壁表面被冷气膜全部覆盖，此时端壁面平均气膜冷却效率相对最高，达到53.7%。     

气膜孔几何结构对涡轮叶片气膜冷却影响的研究进展

综述了近年来涡轮叶片气膜孔几何结构对气膜冷却特性影响的研究成果,介绍了影响气膜冷却效果的因素.总结了气膜孔结构对叶片前缘、叶片端壁以及对平板气膜冷却影响的研究现状.阐述了气膜孔结构对气膜冷却传热特性的影响.最后指出进一步优化气膜孔结构,综合考虑气膜孔尺寸、长度、间隔、形状以及相对透平叶片取向对气膜冷却的影响和新型气膜孔的研究.将是今后工作的重点.     

冷却空气量对涡轮冷却性能影响综述

涡轮冷却技术被广泛应用于航空发动机及燃气轮机涡轮研发中,冷却空气的引气量成为影响整机效率的重要因素之一。本文基于现代燃气轮机及航空发动机涡轮叶片采用外部冷却与内部冷却结合的复合冷却的技术发展背景,综述了国内外在冷却空气量对涡轮叶片冷却性能影响方面的研究进展,分析并总结了冷却空气量对气膜冷却、交错肋冷却以及对综合冷却效率的影响规律,并对未来的研究方向给出了一定的建议。分析表明：对气膜孔形状的探索是未来气膜冷却技术研究的重点;交错肋研究主要处于定性研究阶段,对定量研究方法的探索是目前的发展趋势;对综合冷却效率的研究还处于起步阶段,未来可以从外部冷却和内部冷却之间的相互作用关系方面对综合冷却效率开展进一步的研究。     

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。     

Influence of Turbulators in Blade Cooling Passages on Film Hole Discharge Coefficients

This paper details the results of a joint project between Rolls-Royce Deutschland (RRD) and the Northwestern Polytechnical University of China (NWPU). The objective of the project was the determination of the influence of tabulators in turbine blade cooling passages on film hole discharge coefficients (Cd coefficients). A large-scale plexiglas model was used by the NWPU to measure the turbulator influence on Cd coefficients for a wide range of different geometrical parameters, Reynolds numbers and cooling flow off take ratios. RRD specified the comprehensive test matrix and analysed the test data. The CFD code FLUENT was used by RRD for numerical simulation of the test cases with the main objective to support the interpretation of observed trends. Both, experimental and numerical results will be presented in this paper for a selection of test configurations.     

叶型表面曲率对离散孔气膜冷却性能的影响

由于型面曲率的影响,涡轮叶片前缘和吸力面的冷却气膜易于脱离型面,气膜冷却效果下降。本研究将叶片型线分段拟合,建立了多个单一曲率的曲面模型(R/D=-30、-75、120、∞),研究涡轮叶片表面曲率对于气膜冷却的影响。流动与传热的数值模拟采用Fluent软件,湍流模型选择RNGk-ε模型,模拟方法经平板流动进行的结果验证是可靠的。在不同吹风比(M=0.5、1.2、2.0)条件下,计算比较了不同曲率曲面上气膜单孔下游的壁面传热系数以及局部平均气膜冷却效率。结果表明:涡轮叶片型面曲率对气膜冷却效果的影响与吹风比有关。不同曲率的型线部分,应该设计采用不同的吹风比,气膜冷却效果可能取得最佳。低吹风比M<1时,凹面曲率对气膜换热系数是强化,凸面基本没有作用。高吹风比M>1时,曲率不影响换热能力,冷却效果则取决与气膜相对于型面的流动状态和与主流的掺混能力。     

Experimental investigation on the leading edge film cooling of cylindrical and laid-back holes with different hole pitches

Experimental investigation has been performed to study the film cooling performances of cylindrical holes and laid-back holes on the turbine blade leading edge. Four test models are measured for four blowing ratios to investigate the influences of film hole shape and hole pitch on the film cooling performances Film cooling effectiveness and heat transfer coefficient have been obtained using a transient heat transfer measurement technique with double thermochromic liquid crystals. As the blowing ratio increases, the trajectory of jets deviates to the spanwise direction and lifts off gradually. However, more area can benefit from the film protection under large blowing ratio, while the is also higher. The basic distribution features of heat transfer coefficients are similar for all the four models. Heat transfer coefficient in the region where the jet core flows through is relatively lower, while in the jet edge region is relatively higher. For the models with small hole pitch, the laid-back holes only give better film coverage performance than the cylindrical holes under large blowing ratio. For the models with large hole pitch, the advantage of laid-back holes in film cooling effectiveness is more obvious in the upstream region relative to the cylindrical holes. For the cylindrical hole model and the laid-back hole model with the same hole pitch, heat transfer coefficients are nearly the same with each other under the same blowing ratios. Compared with the models with large hole pitch, the laterally averaged film cooling effectiveness and heat transfer coefficient are larger for the models with small hole pitch because of larger proportion of film covering area and strong heat transfer region.     

Influence of Trenched Shaped Holes on Turbine Blade Leading Edge Film Cooling

Computational results are presented for a row of coolant injection holes on each side of a high-pressure turbine blade near the leading edge. Seven hole configurations have been used to show the effect of various diffusion shaped holes and their trenching on film cooling effectiveness: (1) cylindrical film hole; (2) forward diffused film hole; (3) trenched forward diffused film hole; (4) conically flared film hole; (5) trenched conically flared film hole; (6) laterally diffused film hole; and (7) trenched laterally diffused film hole. Computational solutions of the steady, Reynolds-averaged Navier–Stokes equations are obtained using a finite-volume method. Results show that the main effect of trenching is the reduction of jet lifting off from the blade surface and so the prevention of sudden lowering of cooling effectiveness after the injection location. Moreover, hole trenching has more effect on film cooling flow on the suction side than on the pressure side. Also, the trenched laterally diffused shaped hole has the highest laterally averaged effectiveness on both the suction side and the pressure side of the blade.     

燃气轮机透平叶片传热和冷却研究：内部冷却

随着燃气轮机透平进口温度的不断提高,其换热与冷却问题已然成为现代高性能燃气轮机研发中亟待解决的核心关键技术之一.透平叶片的冷却可以分为内部冷却和外部冷却,结合作者近年的研究工作,详细综述了燃气轮机透平叶片内部换热与冷却问题的研究现状与进展,着重介绍了叶片内部蛇形通道冷却、叶片内部冲击冷却和前缘的旋流冷却及尾缘柱肋冷却,指出了它们各自在相关方面需要进一步开展的工作.其中：在蛇形通道冷却方面,需要进一步研究旋转状态下蛇形通道内流动与换热特性、发展高性能的扰流装置及通道弯头结构、设计新颖高效的叶顶内部冷却结构、获得带气膜孔或冲击孔的蛇形通道内的换热与冷却特性;在叶片前缘内部冲击冷却方面,需要研究不同曲率面上的冲击冷却换热特性、旋转条件下的冲击冷却以及冲击气膜复合冷却特性;在旋流冷却方面,需要对其结构参数的影响开展进一步的广泛研究,并开展旋转状态下旋流冷却特性的研究;在尾缘柱肋冷却方面,需要进一步研究复杂流场下柱肋阵列通道中的流动换热与众敏感因子之间的关系.     

Gas Turbine Blade Tip Heat Transfer and Cooling: A Literature Survey

Gas turbines are widely used for aircraft propulsion, land-base power generation, and other industrial applications like trains, marines, automobiles, etc. To satisfy the fast development of advanced gas turbines, the operating temperature must be increased to improve the thermal efficiency and output work of the gas turbine engine. However, the heat transferred to the turbine blade is substantially increased as the turbine inlet temperature is continuously increased. Thus, it is very important to cool the turbine blades for a long durability and safe operation. Cooling the blade must include cooling of the key regions being exposed to the hot gas. The blade tip region is such a critical area and is indeed difficult to cool. This results from the tip clearance gap where the complex tip leakage flow occurs and thereby local high heat loads prevail. This paper presents a literature survey of blade tip leakage flow and heat transfer, as well as research of external and internal cooling technologies. The present paper does not intend to review all published results in this field, nor review all papers from the past to now. This paper is limited to a review of recently available published works by several researchers, especially from 2001 to present, concerning blade tip leakage flow associated with heat transfer, and external or/and internal tip cooling technologies.     

Investigation of the Conjugate Heat Transfer and Flow Field for a Flat Plate with Combined Film and Impingement Cooling

Film cooling combined with internal impingement cooling is one of the most effective technologies to protect the gas turbine vanes and blades from the hot gas. In this study, conjugate heat transfer CFD study was undertaken for a flat plate with combined film cooling and impingement cooling. An experiment on conjugate heat transfer of a flat plate with combined film and impingement cooling was performed to validate the code. Then the effects of several parameters including Biot number, blowing ratio, film hole shape and impingement hole diameter on the overall cooling effectiveness were numerically studied. The results show that for a specific combined cooling scheme and a given blowing ratio, the coolant potential can be reasonably allocated to the internal and the external cooling to achieve the overall cooling effectiveness. As the blowing ratio increases, the overall cooling effectiveness trends to reach a maximum value. For different film hole geometrical, the maximum values of the overall cooling effectiveness at high blowing ratio approximate to the same value. At a given mass flow rate of coolant, the increase of the impingement hole diameter leads to the reduction of the overall cooling effectiveness.     

On the improvement of film cooling performance using tree-shaped network holes: A comparative study

Abstract

For modern high-efficiency gas turbines, film cooling is an essential method to protect the turbine blade from the hot gas, and the issue about how to improve the film cooling performance has attracted much attention. This study presents a new design concept used for film cooling in gas turbine to improve the overall cooling effectiveness and better decrease the metal temperature of the blade at the same time. A tree-shaped film cooling structure is considered. To validate the superiority of the proposed structure, a series of numerical simulation cases are conducted at three typical blowing ratios (i.e. 0.5, 0.764, and 0.9). The first case is a film cooling channel with a single film hole with a diameter of 5?mm and it is inclined by α?=?45° relative to the mainstream direction and the other three cases are tree-shaped structures with one level, two levels and three levels of bifurcations. Moreover, the same boundary conditions and turbulence model (realizable k–ε) are adopted, and three-dimensional numerical simulations are used for all cases. The computed results show that the higher the blowing ratio, the better is the overall effectiveness downstream the film holes of the tree-shaped structures, whereas the opposite is valid for the case with a single film hole. Additionally, the overall effectiveness of the tree-shaped structures is improved more than 50% compared with Case 1 with a single film hole, and the results also demonstrate that the more levels of the structure, the lower the metal temperatures will be. Therefore, it is indicated that this research will make a contribution to a higher performance gas turbine.