检索结果-南通市图书馆

Experimental investigation of the full coverage film cooling effectiveness of a turbine blade with shaped holes

在线全文

维普期刊数据库

学校读者我要写书评

暂无评论

Chinese Journal of Aeronautics 2022年第3期35卷 297-308页

作者： Cunliang LIU Fan ZHANG Shuaiqi ZHANG Qingqing SHI Hui SONG School of Power and Energy Northwestern Polytechnical UniversityXi'an 710129China Shaanxi Key Laboratory of Thermal Sciences in Aero-engine System Xi'an 710129China Beijing Institute of Radio Measurement Beijing 100854China

The film cooling effectiveness of two turbine blades at different turbulence intensities(0.62%and 16.00%)and mass flux ratios(2.91%,5.82%,8.73%and 11.63%)is studied by using the Pressure-Sensitive Paint(PSP)measurement *** are a baseline and an improved turbine blade in current work,and their film cooling hole position distribution is the *** the hole shape on suction surface and pressure surface is changed from cylindrical hole(baseline)to laid-back fan-shaped hole(improved blade).Both blades have 5 rows of cylindrical holes at the leading edge and 4 rows of cooling-holes on the suction surface and the pressure *** experimental results show that the film cooling effectiveness of the improved blade is much better than the *** increase in turbulence intensity will reduce the cooling effectiveness on the surface of turbine blade,but the effect of turbulence intensity becomes weaker with an increase in the mass flux *** with the multiple rows of cylindrical holes,the cooling effectiveness of shaped holes is more influenced by the turbulence intensity at low mass flux ratio.

关键词： Adiabatic film cooling effectiveness Film cooling Shaped holes turbine blade Turbulence intensity

Finite Element Simulation on Thermal Fatigue of a turbine blade with Thermal Barrier Coatings

在线全文

学校读者我要写书评

暂无评论

Journal of Materials Science & Technology 2014年第4期30卷 371-380页

作者： L.Yang Q.X.Liu Y.C.Zhou W.G.Mao C.Lu Key Laboratory of Low Dimensional Materials & Application Technology(Ministry of Education) Xiangtan University Faculty of Materials Optoelectronic & PhysicsXiangtan University Department of Mechanical Engineering Curtin University

In this paper, a finite element model was developed for a turbine blade with thermal barrier coatings to investigate its failure behavior under cyclic thermal loading. Based on temperature and stress fields obtained from finite element simulations, dangerous regions in ceramic coating were determined in terms of the maximum principal stress criterion. The results show that damage preferentially occurs in the chamfer and rabbet of a turbine blade with thermal barrier coatings and its thermal fatigue life decreases with the increase of thermal stress induced by high service temperature.

关键词： turbine blade Thermal barrier coatings Finite element model Thermal fatigue Life prediction

Research on the intelligent design system for investment casting die of aero-engine turbine blade based on knowledge

在线全文

学校读者我要写书评

暂无评论

航空动力学报 2010年第5期25卷 1061-1067页

作者： JIANG Rui-song ZHANG Ding-hua WANG Wen-hu The Key Laboratory of Contemporary Design and Integrated Manufacturing Ministry of EducationSchool of Mechanical EngineeringNorthwestern Polytechnical UniversityXi'an 710072China

To solve the problems in turbine blade investment casting die design process such as long design time,lacking of expert experience and low level of intelligence,knowledge-based engineering (KBE) was introduced in the turbine blade investment casting die design field. The key technologies of the intelligent design method were researched and a prototype system was developed. A hybrid reasoning model was prompted in which case-based reasoning (CBR) was applied to conceptual design and rule-based reasoning (RBR) was applied to parts design after research the design process and domain knowledge of casting die. In the conceptual design stage,a retrieval model which integrated nearest neighbor approach and knowledge-based retrieval approach was prompted to improve the retrieval efficiency. Meanwhile,RBR was used to modify the retrieval result. The practical application results indicate that this system can reuse the expert experience efficiently and heighten the die design efficiency and quality.

关键词： turbine blade investment casting die intelligent design knowledge-based engineering (KBE)

Experimental investigation of aerodynamics of turbine blade trailing edge cooling

在线全文

学校读者我要写书评

暂无评论

航空动力学报 2010年第5期25卷 1097-1102页

作者： SUN Da-wei QIAO Wei-yang DONG Kang-tian XU Kai-fu School of Power and Energy Northwestern Polytechnical UniversityXi'an 710072China Xi'an Thermal Power Research Institute Xi'an 710032China

This paper presented an experimental investigation the effects of the trailing edge cooling on the aerodynamic performance. The experiments were conducted on the low-speed linear cascade tunnel at Northwestern Polytechnical University. The external aerodynamic characteristics in the 40 percent chord downstream of exit plane were measured using five-hole probe with the different ejection rates. The results showed that the total pressure loss coefficient at the middle spanwise plane increased at first and then it has a decreasing tendency with the increase of ejection ratio. The trailing edge cooling would influence the structure of the turbine cascade outlet flow field. When the ejection rate was 3%,the loss area near the blade endwall would become stronger,but it would become weaker with the 6% ejection ratio. On the whole,the trailing edge cooling had more influence on the profile loss than on the secondary loss.

关键词： turbine blade trailing edge cooling profile loss secondary loss

The cooling performance of three-row compound angle holes on the suction surface of a rotating turbine blade

在线全文

学校读者我要写书评

暂无评论

Propulsion and Power Research 2021年第1期10卷 23-36页

作者： Zhiyu Zhou Haiwang Li Gang Xie Shuangzhi Xia Jianjun Zhou National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics School of Energy and Power EngineeringBeihang UniversityBeijing100191China Beihang University Beijing100191China New Era Engineering Consulting Co. LtdBeijing100088China Shenyang Aeroengine Research Institute Aero Engine Corporation of ChinaShenyang110015China

Experiments were carried out to study the effects of compound angle,hole arrangement,and blowing ratio on the film cooling performance of multiple rows of holes on the suction surface of a turbine *** turbine worked at rotational speed of 600 rpm corresponding to the rotational Reynolds number of 5.36*** rows of cylindrical holes arranged in line or in stagger were drilled on the rotor blade suction surface at the streamwise location of 12.4%,17.8%,and 23.2%,*** compound angles,with the same streamwise angle of 45but different lateral deflection angles of 45,0,and45,were stud*** film cooling effectiveness was obtained using pressure sensitive paint(PSP)technique with average blowing ratios varied from 0.5 to *** results showed that the application of compound angle changes the jet direction in the near-hole region and makes the film spread *** with the film cooling without compound angle,using positive and negative compound angle can improve overall average film cooling effectiveness by about 20%and 25%,*** effects of the secondary flow also can be weakened.A stagger film trajectory arrangement can achieve more uniform film coverage with higher overall film cooling *** film trajectory arrangement of a positive compound angle injection is determined by the combined effect of hole arrangement and blowing ***,the film trajectory arrangement of a negative compound angle injection is almost the same as the hole arrangement and nearly does not change with the blowing ratio.

关键词： Film cooling turbine blade Suction surface Compound angle Hole arrangement Blowing ratio

Numerical simulation on vacuum solution heat treatment and gas quenching process of a low rhenium-containing Ni-based single crystal turbine blade

在线全文

维普期刊数据库

学校读者我要写书评

暂无评论

China Foundry 2016年第6期13卷 402-413页

作者： Zhe-xin Xu Xiang-lin Su Qing-yan Xu Bai-cheng Liu Key Laboratory for Advanced Materials Processing Technology (Ministry of Education) School of Materials Science and Engineering Tsinghua University

Numerical heat-transfer and turbulent flow model for an industrial high-pressure gas quenching vacuum furnace was established to simulate the heating, holding and gas fan quenching of a low rhenium-bearing Ni-based single crystal turbine blade. The mesh of simplified furnace model was built using finite volume method and the boundary conditions were set up according to the practical process. Simulation results show that the turbine blade geometry and the mutual shielding among blades have significant influence on the uniformity of the temperature distribution. The temperature distribution at sharp corner, thin wall and corner part is higher than that at thick wall part of blade during heating, and the isotherms show a toroidal line to the center of thick wall. The temperature of sheltered units is lower than that of the remaining part of blade. When there is no shelteration among multiple blades, the temperature distribution for all blades is almost identical. The fluid velocity field, temperature field and cooling curves of the single and multiple turbine blades during gas fan quenching were also simulated. Modeling results indicate that the loading tray, free outlet and the location of turbine blades have important influences on the flow field. The high-speed gas flows out from the nozzle is divided by loading tray, and the free outlet enhanced the two vortex flow at the end of the furnace door. The closer the blade is to the exhaust outlet and the nozzle, the greater the flow velocity is and the more adequate the flow is. The blade geometry has an effect on the cooling for single blade and multiple blades during gas fan quenching, and the effects in double layers differs from that in single layer. For single blade, the cooing rate at thin-walled part is lower than that at thick-walled part, the cooling rate at sharp corner is greater than that at tenon and blade platform, and the temperature at regions close to the internal position is decreased more slowly than

关键词： Ni-based superalloy incipient melting cooling rates turbine blade

Effect of surface roughness on the aerodynamic performance of turbine blade cascade

在线全文

学校读者我要写书评

暂无评论

Propulsion and Power Research 2014年第2期3卷 82-89页

作者： Tao Bain Jingyuan Liu Weihao Zhang Zhengping Zou National Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamics 2011 collaborated innovation center of advanced aero-engineSchool of Energy and Power EngineeringBeihang UniversityBeijing 100191China

The effect of surface roughness on the boundary development and loss behavior of turbine blades is investigated with different Reynolds numbers in this *** result shows that the velocity profile in boundary layer is plumper on rough surface than on smooth *** aerodynamic loss is lowered at low Reynolds number,but becomes significantly large at high Reynolds *** total pressure loss coefficient of cascade can reach a top increase of 129%for rougher blades comparing with smooth blades at Re=300000.

关键词： turbine blade Surface roughness Boundary layer Reynolds number Aerodynamic loss

Extremum selection method of random variable for nonlinear dynamic reliability analysis of turbine blade deformation

在线全文

维普期刊数据库

学校读者我要写书评

暂无评论

Propulsion and Power Research 2012年第1期1卷 58-63页

作者： Chengwei Fein Guangchen Bai School of Energy and Power Engineering Beihang UniversityBeijing 100191China

To effectively select random variable in nonlinear dynamic reliability analysis,the extremum selection method(ESM)is ***,the basic idea was introduced and the mathematical model was established for the *** nonlinear dynamic reliability analysis of turbine blade radial deformation was taken as an example to verify the *** results show that the analysis precision of the ESM is 99.972%,which is almost kept consistent with that of the Monte Carlo method;moreover,the computing time of the ESM is shorter than that of the traditional ***,it is demonstrated that the ESM is able to save calculation time and improve the computational efficiency while keeping the calculation precision for nonlinear dynamic reliability *** present study provides a method to enhance the nonlinear dynamic reliability analysis in selecting the random variables and offers a way to design structure and machine in future work.

关键词： Extremum selection method(ESM) turbine blade Radial deformation Reliability analysis Random variable Nonlinear Dynamic

A turbine blade Parametric Modeling Method Considering 1-D Heat Transfer Analysis

在线全文

维普期刊数据库

学校读者我要写书评

暂无评论

Computer Aided Drafting,Design and Manufacturing 2015年第3期25卷 1-9页

作者： LI Ji-xing XI Ping GUO Yan-fei ZHANG Jian-qi School of Mechanical Engineering and Automation Beihang University School of Software Engineering Beihang University School of Mechanical Engineering Northwestern Polytechnical University

Traditional feature-based turbine blade models can match the needs of geometric modeling but could hardly meet the requirement of data extraction in 1-D heat transfer analysis. In this paper, the requirements of data extraction in 1-D heat transfer analysis are taken into consideration as well as geometric representation in parametric design process. An improved turbine blade parametric modeling method is proposed. Based on the modeling method proposed, a system structure of blade modeling process considering 1-D heat transfer analysis is devised. Eventually, a turbine blade parametric modeling system is constructed to test and verify the feasibility of the proposed modeling method and system structure. Experiments show that the blade parametric modeling method proposed can make geometric models better adapt to the specific requirements of 1-D heat transfer analysis and has certain reference value to the creation of high quality digital models.

关键词： turbine blade parametric modeling 1-D heat transfer analysis data extraction