tip clearance 中文意思是什麼
tip clearance
解釋
齒頂間隙-
The vortex simulated in this article include the shedding vortex induced by the vane trailing edge boundary layer, the endwall vortex generated by the endwall boundary layer interaction, the passage vortex generated by the rotor rotation, and the leakage vortex generated by the tip clearance flow
渦輪級內的渦運動包括：導向器葉片尾緣附而層引起的脫落渦；轉子通道內轉子的旋轉運動產生的通道渦；根腳區兩個端壁附面層干涉，形成的根腳渦；存在葉尖漏流時，出現的漏流渦。 -
An interpolation program is used to convert the fluent result data to the ansys load data. it is a new method to analyze turbine tip clearance. in this paper, some research of the numerical computation of the tip clearance of aero - engine is done, the parametric method is used and the research on the flow, heat and structure integration analyses is accomplished
本文對渦輪機匣氣熱固一體化分析方法做了研究，通過編制了載荷轉換與施加程序，從氣熱計算模型中提取溫度場計算結果，並作為載荷加入到熱固耦合計算模型中，實現了高壓渦輪機匣的一體化計算分析，為實現渦輪葉尖間隙的氣熱固一體化分析打下了基礎。 -
The result of the calculation for tip clearance is reasonable when it is compared with theory. two ways are put forward for convention of dimension of the turbine components from high temperature to low one, which is related with tip clearance, a simple example is used to illuminate that the two ways are useful, using the method of design optimization, axiisk and a blade of a certain turhine is analysed, it showes that the method of design optimization is feasible to be used for convertion of dimension of the turbine components. finally, ansys software is used to analyzed the variation of tip clearance with the method of cyclic symmetry analysis when engine works under the conditions of temperature and rotational speed, am using a new method to deal with thermal contact resistance in the calculation
本文完善了計算渦輪葉尖間隙的簡化演算法程序，增加了程序的計算功能，並將其應用於某高壓渦輪進行葉尖間隙分析，所得結果與理論結果進行了對比，得出修改後的程序用於葉尖間隙計算是合理的；同時提出了與葉尖間隙相關的渦輪典型部件的冷、熱態的尺寸兩種換算方法，使用優化設計的方法進行了實例分析，說明了所提出的計算方法是可行的；最後應用ansys有限元軟體利用循環對稱的方法分析了某型發動機高壓渦輪在溫度場及離心力作用下的葉尖間隙在發動機工作過程中變化情況，並分析了計算中的接觸熱阻的處理問題。 -
Twelve casing configurations were investigated, consisting of three step profiles at each of three clearance levels ( including seven casing geometric size ) to find the effects of radial / axial variation of tip gap on rotor performance, and five casing configurations including two types of asymmetric profiles were applied in the research of circumferential variation of tip clearance
文中設計了十二種機匣結構用於與實壁機匣相比較，包括軸向布局的七種階梯狀結構及五種周向變化的不對稱結構形式（偏心周向變化和橢形周向變化） 。 -
Experimental and numerical study of wall flow pattern of turbine cascade with tip clearance
有間隙渦輪葉柵壁面流譜實驗與數值模擬研究 -
The complex vortex system structure and shock wave system structure inside this rotor is obtained. wall flow patterns on the blade surface and hub surface are found out. the complex vortex system structure, such as horseshoe vortex, passage vortex, corner vortex and trailing vortex, and the interaction with shock wave system are researched. especially, the character of the tip clearance flow inside the rotor passage is revealed, and the interaction between shock wave and tip clearance flow near blade tip and the evolution of tip clearance flow are considered
給出了葉片表面及輪轂面上的壁面流型，分析並揭示了轉子葉道內的馬蹄渦、通道渦、角渦、尾渦等復雜渦系及其與激波的相互干涉；特別是，分析並揭示了轉子葉道內頂隙射流的特點，得到了頂隙附近激波與泄漏流動的干涉形態及泄漏流動的發展，並著重給出了其與激波的干涉形態。 -
The parametric method is used in the process of turbine parts modeling and tip clearance analysis. due to the complexity of the turbine parts, some characters are predigested
本文引入了近年來迅速發展的參數化設計思想，應用於渦輪部件的建模和葉尖間隙的分析。 -
In this paper, the status quo of the tip clearance of aero - engine is surveyed, the theory and the method of the numerical computation of tip clearance are introduced, the simple tip clearance calculation program is modified and refined and the computation method of the turbine temperature field is improved
本文闡述了國內外航空發動機葉尖間隙的研究現狀，介紹了渦輪葉尖間隙計算的理論和方法。對渦輪葉尖間隙準二維計算程序作了修改和完善，改進渦輪部件溫度場的計算方法，增加了變量顯示/修改、程序控制和結果顯示界面，使軟體更加直觀，實用。 -
A simplify high pressure turbine ( hpt ) tip clearance model is analyzed with the cyclic symmetry method. research on the flow, heat and structure integration analyses is achieved in this paper. flow / heat analysis is done by fluent software, and heat / structure analysis is done by ansys software
針對渦輪部件的結構特點，進行了適當的簡化，利用參數化設計思想建立了渦輪葉尖間隙計算模型，用循環對稱的方法分析了某型發動機高壓渦輪葉尖間隙在工作過程中變化的情況。 -
Numerical study of vortex structure within turbine cascade with tip clearance
有間隙渦爐葉柵渦系結構的數值模擬 -
Abstract : a 3d numerical solution of transonic turbulent flowfield inside a compressor rotor is analyzed with a consideration of blade tip clearance
文摘:藉助于考慮葉片頂部間隙的壓氣機轉子內跨音速湍流流場的三維數值解，得到了該轉子流場中的復雜渦系與波系結構。 -
On the basis of above work, by using of " thin blade approximation ", a 3d viscous code had been developed to calculate flow field in rotor with tip clearance
在以上工作的基礎上，採用「薄葉片」假設，發展了一種用於計算考慮頂部間隙的壓氣機轉子內部流場的三維粘性程序。 -
Development of rotating linear cascade facility for simulating blade tip clearance flow
模擬葉尖間隙流的轉動平面葉柵實驗方案 -
Asymmetric profiles of tip clearance have little influence on rotor peak efficiency, and the degree of degredation is in rat io of the level of asymmetry at circumferentioal direction
轉子尖部間隙周向布局的變化對失速裕度及效率的變化起負面影響，且隨著周向變化的程度加大，這個惡化趨勢也加大，但對峰值效率的影響較小。 -
Tip clearance has much effect on the properties of aero - engine. as the reference of the project design, the numerical computation of tip clearance can improve the aero - engine performance, reliability and to reduce the specific fuel consumption ( sfc )
葉尖間隙對航空發動機性能有較大的影響，研究葉尖間隙的數值分析技術可以為工程設計提供參考，從而提高航空發動機的工作性能、可靠性和耐久性。 -
The stepped location and radial depth of tip clearance are crucial parameters to decide rotor stability and performance
階梯狀間隙的開槽位置及徑向的間隙深度是影響轉子性能和穩定性的重要參數。 -
Blade tip clearance
葉尖與船體的間隙 -
It was found that the introduce of tip clearance deteriorate the overall performance of the compressor rotor
數值結果表明葉頂間隙的引入惡化了壓氣機轉子的性能。 -
The influence of tip clearance on overall performance and detailed flow structure in tip region of an axial compressor rotor was investigated
研究了頂部間隙對壓氣機轉子總性能及內部流場的影響。 -
Research findings about the tip clearance of engine in the paper are basal, they can be used as reference of control the tip clearance
本文對發動機的葉尖間隙分析做了一些基礎性工作，對于葉尖間隙控制方面的研究有一定的參考價值。
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