axial flow effect 中文意思是什麼
axial flow effect
解釋
軸流效應-
4 ) in a pre - swirl rotator - stator cavities with discrete pre - swirl nozzles and blade - cooling entry holes, the influences of pre - swirl angle and flow parameter on the flow and heat transfer characteristics were numerically investigated. the correlation for average nusselt number vs rotating reynold number or non - dimensional mass flowrate were established. the results show that : advantage of per - swirl inflow is the effect of cooling the blade - cooling entry holes ; pre - swirl inflow increases heat transfer in rotating disk of pre - swirl chamber ; as pre - swirl angle increases, local nusselt number decreases in pre - swirl chamber ; the temperature of stator of inner rotator - stator chamber and per - swirl chamber decreases as rotating reynold number increases ; when the axial mass flowrate maintains constant, heat transfer in the rotating disk of inner rotator - stator cavities does n ' t change as per - swirl mass flowrate increases, while heat transfer in the rotating disk of per - swirl chamber increases ; when the pre - swirl mass flowrate maintains constant, change of the axial mass flowrate has effect on the whole cavity
結果表明，預旋進氣的優點在於增強了葉片冷卻孔附近的對流換熱效果，局部努謝爾數隨預旋角的增大而有所減小；隨旋轉雷諾數的增加，不論是內轉靜腔室還是預旋腔室的靜盤上的溫度都不同程度的降低：當軸向中心進氣質量流量不變時，隨預旋進氣的質量流量增加，內轉靜腔室的轉盤盤面上的換熱基本沒有變化，而預旋腔室的轉盤盤面上的換熱效果增強；當預旋進氣質量流量不變時，軸向中心進氣的質量流量的改變對整個盤腔都有影響。 -
The effect of air distributor on the flow fields was studied with emphasis. the working conditions of the bubble column simulated in the numerical study were as same as in the experiments. the velocity profile at axial direction showed a peek in the center, and a backward flow near the wall when usl / usg < 19. 6
鼓泡塔內軸向液相速度的徑向分佈呈塔中心峰值、壁面附近倒流形式，且與氣相折算速度大小有關，當液相折算速度一定時，隨氣相折算速度增大而愈加陡峭，返混也劇烈。 -
The effect of leakage flow due to the upstream hub axial gap on the rotor performance and the mechanism of interaction between the hub leakage flow and the rotor blade passage flow were studied based on the numerical simulations of the flow fields of a transonic compressor rotor with upstream hub leakage
摘要為研究壓氣機轉子上游葉根軸向間隙泄漏流對轉子性能的影響程度以及泄漏流與轉子流場之間的相互作用機制，對帶有葉根泄漏流的跨聲壓氣機轉子流場進行了數值模擬。 -
Under the condition mention in this physical model, when there is a high rotor heat load, the effect of the axial direction gas - flow to the total heat - emitting capability is not very great
轉子高熱負荷條件下，該模型建模條件下由氣隙楔度所產生的軸向風量對總散熱能力的貢獻較小。 -
The effect of tip injection on the performance of an axial - flow compressor was performed numerically
採用數值模擬方法研究了頂部噴氣對某軸流壓氣機氣動性能的影響。 -
When the rotation has the same direction with the axial velocity, the effect of rotation enforces the intensity of secondary flow and the heat convection, the friction factor and the nusselt number increases as f increase ; when the rotation has the opposite direction with the axial velocity, the flow structure becomes more complicated, for f = 1. 2, the complicated structure of secondary flow generates, the friction facior and nusselt number almost has the same value of stationary straight pipe
當旋轉方向和主流方向相同時，旋轉的作用加強了二次流的強度，使得管道摩擦系數變大，管道換熱效果增強；當旋轉方向和主流方向相反時，管道內流動結構變化十分明顯， f - 1 . 2時，流動結構最為復雜，摩擦系數降至最低，換熱效果最弱。 -
By using a reynolds - averaged two - dimensional computation, the effect of upstream wake on unsteady separated flow field of downstream adjacent vanes was investigated in low - speed axial compressor
摘要利用二維數值模擬研究了低速軸流壓氣機上游尾跡對下游相鄰葉排的非定常分離流場的影響。 -
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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