velocity of blade 中文意思是什麼
velocity of blade
解釋
葉片速度-
As we know, inverse techniques make blade ' s profile well compatible with its surface velocity distribution, however, they give designers big challenges that the ideal velocity distribution is hard to obtained and sometimes the non - physical solution, such as double covering of flow field or unclosed profiles, would come out. the proposed design procedure in the paper has avoided the disadvantage mentioned above. in this paper, a quasi - irrotational equation is used to describe the flow in cascade instead of the generally used irrotational equation
眾所周知，一般的反問題和混合問題的最大特點，是在給定的壓力面和吸力面上的壓力分佈或速度分佈條件下，直接得到葉片的幾何形狀，它可以使葉型型面與表面氣流參數有機結起來；其不足之處在於，對設計者而言，很難給定理想的葉片表面壓力分佈或速度分佈，並且有時會得到一個非物理解，如：得出的初始葉型可能會出現前緣、尾緣不封閉的現象。 -
The paper analyzes the characteristic of aerodynamics with structure of helicopter propeller blade, dissertrates vortex theory and the theory about gliding air field which produce the power of helicopter propeller blade. at the same time it also deduce the method of computing the induced velocity produced by helicopter propeller blade with vortex theory. at last, an influcence to the spreading of sound is discussed
並且將兩種定位演算法進行了比較，說明了優劣；結合直升機的結構分析了旋翼的空氣動力特性，論述了直升機旋翼產生拉力的滑流理論和渦流理論，結合渦流理論論述了直升機旋翼流場誘導速度的計算方法，在此基礎上分析了直升機旋翼流場對聲音傳播的影響。 -
The blade inner channel cooling is a complex convection - conduction coupling problem. this thesis build a three - dimension. compressible turbulence model, and give a general solve method. with the geometrical model of the glossily rectangle straight channel, the rectangle straight channel with in - line arrays disturb plates, the rectangle straight channel with staggered arrays disturb plates, the rectangle straight channel with slant disturb plates, this thesis compute the flow and heat transfer condition when the cold air path though these channels, and gain the temperature field, pressure field, velocity filed, in addition. this thesis also analyze the influence of the different channel height, the different channel materials, the different channels, and gain the function relation between he nusselt number, friction factor and reynolds number. this thesis is emphasis on the new heat transfer enhancement structure, that is, disturb plates, with the comparison with the glossily channel and channel with pin fins, the heat transfer enhancement effect of the former is better, and the conclusion can be used in the design of aircraft blade
葉片內部通道冷卻是一個復雜的對流?導熱耦合傳熱問題，本文在分析葉片內部通道冷卻的流動與傳熱情況的基礎上，建立了三維、可壓縮紊流的物理模型，得到了通用的求解辦法；利用不帶擾流片的矩形直通道、帶順排擾流片矩形直通道、帶叉排擾流片、帶傾斜擾流片的矩形直通道的幾何模型，計算了冷卻空氣通過這幾種通道時的流動與換熱情況，得到了各種不同情況下計算區域的溫度場、壓力場、速度場；在此基礎上分析了不同的通道高度、不同的葉片通道材質對葉片內部通道冷卻的影響，並整理得到了各種通道形式下，努謝爾數和阻力因子與雷諾數的函數關系；本文重點研究了新型的葉片內部通道冷卻強化傳熱措施?帶擾流片的內部冷卻通道的強化傳熱效果，通過與光滑矩形直通道、帶針肋通道的冷卻效果的比較，表明了這種新型鮚構的優勢，對于葉片內部通道冷卻結構的設計可以起到指導的作用。 -
When the propeller operates in the spatially non - uniform velocity field behind the ship, the unsteady cavitation on the blades often causes the vibration of ship structure, the propeller noise and the cavitation erosion on the blade
在船尾非均勻流場中工作的螺旋槳，常常由於槳葉上產生了非定常空泡，導致船尾振動和螺旋槳噪聲，致使槳葉表面出現空泡剝蝕。 -
The main object of this paper is to design a diagonal impeller, which requires small size and high rotating speed the first step of design is to solve the radial distribution of parameters at the inlet and outlet of the blade, such as pressure, temperature and velocity. and then, according to the radial distribution, we can design the diagonal impeller blade. blade elements are defined on a cone, which pass through the blade edge streamline location
其設計思想是採用準三維設計方法，先進行二維流場計算，在葉片軸向間隙中設立計算站，應用數值計算方法計算葉片前後緣的壓力、溫度、速度等參數沿葉高的分佈，然後根據這些參數，選取若干個回轉面進行葉型設計；再將各回轉面上得到的基元葉型沿某一個積疊軸積疊起來形成三維葉片，最後對得到的三維葉片進行試驗，並對實驗結果進行分析比較。 -
In this paper, based on the navier - stokes equation and the k - turbulent model, the numerical simulation of the 3d turbulent flow in a centrifugal impeller, of which specific speed is 93. the distribution of the velocity and pressure in the blade - to - blade passage are presented at the design and off - design operating conditions. the simulation results were verifiable with the results measured by piv
本文基於n ? s方程和標準的k ?雙方程紊流模型，採用商用cfx - tascflow計算軟體對一離心泵葉輪模型進行了葉輪內部三維紊流數值模擬，得到了三個典型工況下、從輪轂到前蓋板每一個斷面上的速度和壓力分佈。 -
Introduction to the mechanism of cutting blade alignment, tip velocity, sequence of power generation, etc
斬擊的物理入門介紹包括刃筋劍尖加速發力次序等上段 -
Abstract : concerning the models for discribing aerodynamic stability of axial flow compressor, the original model is one - dimensional, and it is reasonable for the onset of surge only. for the onset of rotating stall, there are just some two - dimensional models at published literatures. a three - dimensional aerodynamic of compressor has been presented in this paper. an aerodynamic stability model concerning radial disturbance of compressor is presented. the calculated results show that the occurrence of radial disturbance is related to the axial velocity disturbance, which has important effect on aerodynamic stability of compressor. the position of onset of stall, in blade tip or hub, is dependent upon the characteristics of blade element. the comparisons of calculated results predicted by 2d and 3d aerodynamic stability model have also been made in this paper
文摘:軸流壓氣機的氣動穩定性模型，最初為一維模型，僅適用於描述喘振發作.對于旋轉失速發作，在公開文獻中有一些二維模型發表.本文提出了一類考慮壓氣機徑向擾動對失速影響的新的氣動穩定性模型.計算結果表明壓氣機的軸向擾動往往隨著徑向擾動的產生，徑向擾動的強度影響壓氣機的氣動穩定性，在葉尖還是葉根首先產生失速與壓氣機基元葉柵特性密切相關.本文對軸流壓氣機二維和三維氣動穩定性模型的計算結果進行了對比分析 -
Concerning the models for discribing aerodynamic stability of axial flow compressor, the original model is one - dimensional, and it is reasonable for the onset of surge only. for the onset of rotating stall, there are just some two - dimensional models at published literatures. a three - dimensional aerodynamic of compressor has been presented in this paper. an aerodynamic stability model concerning radial disturbance of compressor is presented. the calculated results show that the occurrence of radial disturbance is related to the axial velocity disturbance, which has important effect on aerodynamic stability of compressor. the position of onset of stall, in blade tip or hub, is dependent upon the characteristics of blade element. the comparisons of calculated results predicted by 2d and 3d aerodynamic stability model have also been made in this paper
軸流壓氣機的氣動穩定性模型，最初為一維模型，僅適用於描述喘振發作.對于旋轉失速發作，在公開文獻中有一些二維模型發表.本文提出了一類考慮壓氣機徑向擾動對失速影響的新的氣動穩定性模型.計算結果表明壓氣機的軸向擾動往往隨著徑向擾動的產生，徑向擾動的強度影響壓氣機的氣動穩定性，在葉尖還是葉根首先產生失速與壓氣機基元葉柵特性密切相關.本文對軸流壓氣機二維和三維氣動穩定性模型的計算結果進行了對比分析
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