Vibration Analysis of a Certain Type of Aero-engine Turbine Blade Based on UG
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Aero engine
Natural frequency
This paper presents the ONE SHOT BLADE® technology introduced in the wind turbine blade manufacturing process in order to reduce the time, and hence the costs required to build the blade. A comparison with respect to the standard process is also highlighted. The aim of this study is to optimize the structural configuration of a 50m length blade, built with this innovative manufacturing technique, providing a feasible design according to the international standard requirements.
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The quality of the blade profile is important for the performance of aero-engine,so that the measurement of the blade profile is highly regarded.Several kinds of special measurement methods are presented in this paper,which focus on the measurement about blade profile,and its application situation,test accuracy,test ability and limitations etc.are surveyed also.
Aero engine
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The paper applies aerodynamic detection method to detect aero-engine nondestructively.In this paper,generating technology of elementary blade,optimization design of 3D blade,airflow parameter distribution criteria of blade surface,alignment between aero performance and blade geometry,numerical simulation method and method of blade research and analysis are tested.The paper validates the methods,improves the blade design and innovates the theory and practice of bla-de profile testing.
Aero engine
Blade element theory
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Turbine blade vibration is the main problem in turbine blade operation.To guarantee safety operation of turbine unit,the static frequency of all orders of each newly manufactured moving blade should be measured and adjusted.Taking the 1 146 mm last stage long blade as an example,specific calculation method for every order of turbine blade static frequency is being presented,while its structure described and vibration characteristics analyzed.
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In today's industrial scenario, Gas Turbine is one of the most important components of auxiliary power plant system.In order maximize the overall performance and efficiency of all modern turbines, which theoretically operate according to Brayton cycle, they are operated at a very high temperature.These temperatures are so high that, which may fall in the region of turbine blade material melting point temperatures.Due to such high temperatures there is a possibility that the turbine blades may get damaged due to produced thermal stresses and presents a possible threat to the turbine system as well as the operators.Hence to ensure safe and reliable working of the turbines an effective and reliable cooling system is necessary.Currently available methods for cooling of the turbine blades include film cooling with impingement cooling for the leading edge, rib turbulated cooling using serpentine passages for the middle portion of the blade and pin fin cooling for the trailing edge of the turbine blades.The cooling mechanism for turbine blades must include cooling for all possible regions which are exposed to hot gas flow.The turbine blade tip is one of the critical regions which are severely exposed to hot gas flow occurring due to the leakage of gases from the clearance gap between the turbine tip and the shroud.Hence the tip of the turbine blade must be cooled effectively to prevent thermal expansion of the turbine blade tip due to heating.This cooling will eventually help to avoid rubbing of blades to the shroud which may cause their wear.In this paper, we will be presenting the review of various efforts made by various authors towards the cooling of the turbine blade tip.The paper includes both, experimental methods developed as well as numerical efforts reported.Various experimental setups developed for turbine blade tip cooling includes the pioneer work of R. S. Bunker [1] to the recent efforts put by the Potdar et al.It has been noted that most of the authors had attempted this kind of problems experimentally only.They have found that the heat transfer can be improved by adding various types of protrusions on the flat plate surface.These added surface essentially help to produce vortex kind of structure and eventually increases the turbulence level near the tip surface.However it is also fact that to carry out the experimentations for various conditions is very costly due to the need of the today's sophisticated measuring devices required to understand and visualize the heat transfer phenomena.On the other hand numerical simulations will provide the detailed visualization and analysis of the heat transfer and flow characteristics for cooling of turbine blade tip.However producing the accurate and reliable results using available CFD software ANSYS-Fluent also need to be reviewedAn attempt here is to explore and present most of the recentcontributions presented by various authors.These reviews will help and provide the detailed guidelines for planned numerical and experimental investigations required for the cooling of turbine blade tip, which help to provide the feasible and practically usable solution for cooling turbine tip.
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A NC process for aero-engine blade is proposed.It is the technique of blisk(blade-disk) pre-manufacturing and segmentation.The process is researched.It is compared with traditional blade NC process.The applied fields of the process and the distribution of blade group are introduced.
Aero engine
Manufacturing process
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In the process of wind turbine operation, the blade needs to withstand various kinds of loads. With wind turbine power kept getting bigger, the strength requirement of the blades become higher. In order to improve the strength of the blade, lots of new composite materials are use in blade material component parts. This paper studies the geometry laminated structure, external and structural characteristics of composite blade.
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Based on the design and processing of aviation engine blade cooling air film hole,and metrology project technology research and test research,this paper briefly introduces the of idea blade film hole position accuracy detection technology to solve the quantity value transfer and traceability problem in blade film hole processing,make our country achieves major breakthrough in the blade surface aperture measuring domain.
Aero engine
Position (finance)
Traceability
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