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AITEB - An European Research Project on Aero-thermodynamics of Turbine Endwalls and blades

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Journal of Thermal Science 2004年第2期13卷 97-108页

作者： F. HASELBACH H.-P. SCHIFFER Rolls-Royce Deutschland Turbines Eschenweg 11 15827 Dahlewitz GermanyRolls-Royce Deutschland Turbines Eschenweg 11 15827 Dahlewitz Germany

The paper delivers an overview on the European research project AITEB - Aerothermal Investigations on Turbine Endwalls and blades, which started in year 2000 in the course of the 5. Framework Programme (GROWTH). The aim is to submit an integrated technology and design tool package for the advanced, aerothermal highly loaded design of turbines, especially: Experimental/numerical investigation on heat transfer and film-cooling in separated flow for highly loaded blades including advanced trailing edge cooling Heat transfer/ improved cooling of turbine endwalls: Experimental/numerical work on cooling of turbine endwalls, shrouds and recessed blade tips. Optimised CFD-process (drawing-grid-modelling-postprocessing-risk assessment) in order to derive the 'best practice' to use CFD as a time effective tool. After most of the project life, an overview on the project is delivered. Experimental results of test series at various test sites are compared to numerical simulations of the industrial and university partners.

关键词： turbines aerothermal endwalls blades cooling-technology experiment CFD.

Impact analysis of compressor rotor blades of an aircraft engine

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Frontiers of Structural and Civil Engineering 2019年第3期13卷 505-514页

作者： Y B SUDHIR SASTRY B G KIROS F HAILU R BUDARAPU Department of Aeronautical Engineering Institute of Aeronautical EngineeringDundigalHyderabad 500043India Department of Aeronautical Engineering College of EngineeringDefense UniversityBishoftu 1041Ethiopia School of Mechanical Sciences Indian Institute of Technology BhubaneswarBhubaneswar 752050India

Frequent failures due to foreign particle impacts are observed in compressor blades of the interceptor fighter MIG-23 aircraft engines in the Ethiopian air force,supplied by the Dejen Aviation *** this paper,we made an attempt to identify the causes of failure and hence recommend the suitable materials to withstand the foreign particle *** and stress analysis of one of the recently failed MIG-23 gas turbine compressor blades made up of the following Aluminum based alloys:6061-T6,7075-T6,and 2024-T4,has been performed,apart from the impact analysis of the rotor blades hit by a granite *** numerical results are correlated to the practical *** on the modal,stress and impact analysis and the material properties of the three considered alloys,alloy 7075-T6 has been recommended as the blade material.

关键词： axial flow compressor rotor and stator blades aircraft engine stress and impact analysis aluminum alloys

Enhancing the surface hardness and roughness of engine blades using the shot peening process

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International Journal of Minerals,Metallurgy and Materials 2019年第8期26卷 999-1004页

作者： Mohammad A.Omari Hamzah M.Mousa Faris M.AL-Oqla Mohammad Aljarrah Department of Mechanical Engineering Jordan University of Science and TechnologyIrbid 22110Jordan Department of Mechanical Engineering The Hashemite UniversityZarqa 13133Jordan Department of Industrial Engineering The Hashemite UniversityZarqa 13133Jordan

The effects of shot peening on the mechanical properties of steel 1070 were studied to enhance the material’s properties and surface *** this study,pressure and exposure time were the main parameters governing surface hardness and surface *** optimal time duration and pressure were determined after several experimental *** in hardness and surface roughness were monitored as the pressure of the shot and the exposure time were ***,the microstructure was evaluated by scanning electron microscopy(SEM)and the images were enhanced by image processing techniques to evaluate the surface *** charts were constructed to estimate the effects of pressure and time on both surface hardness and surface *** novelty of this study is the concentration on engine blades which are frequently used in aircrafts to determine the optimal time–pressure combination for shot peening to achieve suitable mechanical and surface *** results show that shot peening pressure(up to 482.6 kPa for 7 min)has positive effect on enhancing the surface and mechanical properties for steel 1070 blades;however,an increase in either pressure or time above that level adversely affected both surface hardness and surface roughness.

关键词： shot peening roughness hardness engine blades scanning electron microscopy

A　NEW　METHOD　TO　JUDGE　THE　ENHANCEMENT　OF　HEAT　TRANSFER　IN　THE　TRAILING　EDGE　OF　TURBINE　blades

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Transactions of Nanjing University of Aeronautics and Astronautics 1994年第2期11卷 170-176页

作者： Wang Baoguan(Department of Power Engineering ,NUAA 29 Yudao Street,Nanjing 210016,P.R.China)

An experimental investigation of heat transfer and friction loss with taper pin fin configurations were dealed with. Three kinds of configurations-full cross pin fins (FCF), shorter round pin fins (SRF) and taper pin fins (TPF), with different height md spacing of the fins and friction loss are compared with each other. Besides, a new dimensionless number, the ratio of f to Nu, cslled here the specific friction loss, is put forward to judge the validity of configurations. The comparison obviously shows that:

关键词： heat flux cooling blades pressure drag beat transfer with pin fin experimentation

Comparison of postoperative sore throat following laryngoscopy conducted by Miller and Macintosh laryngoscope blades

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Health 2011年第10期3卷 623-625页

作者： Khosro Barkhordari Farhad Etezadi Reza Shariat Moharari Mohammad Reza Khajavi 不详

BACKGROUND: Post operative sore throat (PST) is one of the most common complaints after tracheal intubation. In this study we compared the effects of curved and straight laryngoscope blades on severity and incidence of PST. METHOD: In this prospective randomized clinical trial we evaluated incidence and severity of PST in 147 ASA physical status I–II, aged 18 – 62 y (group Miller, n = 71), (group Macintosh, n = 76) following intubation with Miller and Macintosh laryngoscope blades by using Visual Analog Scale (VAS). RESULTS: The overall incidence of PST in our study was 35.4% (Macintosh group = 39.5% and in Miller group = 31% and P = 0.829). The incidence of PST was not statistically different between two kinds of laryngoscope blades and the mean rank of pain score was not statistically different in recovery room and up to 48 hours after surgery. CONCLUSIONS: Our study showed these types of laryngoscope blade had not association with incidence and severity of PST. .

关键词： Post Operative Sore Throat Tracheal Incubation Laryngoscope blades

Statistical analysis of the failure modes and causes of the failure blades of the aviation engine

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Statistical analysis of the failure modes and causes of the ...

Gillette Fusion With 5 blades 剃须刀

2012年海峡两岸破坏科学/材料试验学术会议

作者： MA Nan-nan Failure Analysis Center of Aviation Industries of China Beijing Institute of Aeronautical Materials

Based on the failure analysis of Failure Analysis Center of Aviation Industry of China in recent years,the materials selection process in the blades of the aviation engine is illustrated, the common failure modes and causes of the failure blades of the aviation engine are discussed, we found that the 90%of the common failure mode in gas turbine blades and compressor blades is fatigue and these variations may be directly linked to the mechanism of *** paper focuses on the important meaning of failure analysis on the security and reliability of the blades of the aviation *** is discovered that the blades of the aviation engine designs and the procedures of the manufacturer are key points to the security and reliability of the blades in *** further research of comprehensive failure analysis of the blades of the aviation engine can increase the reliability of the blades under the service conditions.

关键词： aviation engine blades failure modes failure reasons

来源： cnki会议评论

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cnki会议

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新潮电子 2005年第20期 76-77页

如果你爱他，就送他Gilletta剃须刀，它坚固、整洁、有力、耐久，一旦拥有，则很难再淡忘。日前，美国吉利（Gillette）公司在MACH3三刀片设计的基础上，推出Gillette Fusion With 5 blades系列剃须刀。

关键词： Gillette Fusion With 5 blades 剃须刀美国吉利公司坚固整洁耐久

Aeroelastic simulation of the first 1.5-stage aeroengine fan at rotating stall

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Chinese Journal of Aeronautics 2020年第2期33卷 529-549页

作者： Feng LIANG Zhifeng XIE Aiguo XIA Ming ZHOU School of Aerospace Engineering Tsinghua UniversityBeijing 100084China Beijing Aeronautical Technology Research Center Beijing 100076China

A massive parallel aeroelastic simulation platform has been built to investigate the first1.5-stage fan of an aeroengine at rotating *** Computational Fluid Dynamics(CFD)solver and Computational Structural Dynamics(CSD)solver are coupled directly by non-matching mesh *** unsteady rotor/stator interaction is solved by the Sliding Mesh Interface *** original rotor blades are shrouded by the midspan *** unshrouded fan is also created to investigate the effects of the midspan *** the shrouded fan and unshrouded fan have stable aeroelasticity at the designed *** rotating stall,the stalled region rotates at 30%of the rotor speed on the absolute reference *** energy spectrum of the rotating stalled flow is measured *** shows that the first two order excitations are much stronger than the higher order *** the flow of rotating stall,the fifth backward travelling wave mode of shrouded fan is resonated by the fifth excitation of the rotational stalled flow because the rotational speed of the stalled region coincides with the modal rotational speed,while for the unshrouded fan,the first bending mode is resonated by the second excitation of the rotational stalled flow,forming two waves in the circumference of the annulus *** rotating stall,the vibration of the shrouded blades is still under control but the vibration of the unshrouded blades is diverged and out of control.A novel tool,i.e.,resonance map,is proposed to predict the *** provides a perspective to explain the effects of midspan shrouds at a theoretical level,and it would also be helpful in the structural design of blades.

关键词： Aeroelasticity Computational Fluid Dynamics Midspan shrouds Rotating stall Turbomachine blades

Numerical Analysis of the Aeroelastic Behaviour for the Last Turbine Stage in 3D Transonic Flow

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Journal of Thermal Science 2004年第4期13卷 328-333页

作者： Vitaly GNESIN Lyubov KOLODYAZHNAYA Institute of Mechanical Engineering Problems of Ukrainian NAS 2/10 Pozharsky St. Kharkov 61046 UkraineInstitute of Mechanical Engineering Problems of Ukrainian NAS 2/10 Pozharsky St. Kharkov 61046 Ukraine

An understanding of the physics of the mutual interaction between gas flow and oscillating blades, and the development of predictive capabilities is essential for improving overall efficiency, durability and reliability. In this study presented the algorithm proposed involving the coupled solution of 3D unsteady flow through a turbine stage and dynamic problem for rotor blades motion by action of aerodynamic forces without separating outer and inner flow fluctuations. There has been performed the calculations for the last stage of the steam turbine under design and off-design regimes. It has investigated the mutual influence of both outer flow non-uniformity and blades oscillations. It has shown that amplitude-frequency spectrum of blade oscillations contains the high frequency harmonics, corresponding to rotor moving one stator blade pitch, and low frequency harmonics caused by blade oscillations and flow non-uniformity downstream from the blade row.

关键词： 3D unsteady flow stator-rotor interaction blades oscillations.