stall flow 中文意思是什麼
stall flow
解釋
失速線-
Additional visual observations are usually in order to establish the advent of unsteady flow, intermittent stall, and full stall.
通常採用另外一些目視法來確定非常定流斷續失速和全失速的出現。 -
Exploring mechanism of stall margin enhancement of subsonic axial - flow compressor through steady micro tip injection
定常微量噴氣提高軸流壓氣機穩定工作裕度機理探討 -
Experimental study of small perturbation induced rotating stall in axial flow compressor
軸流壓氣機小擾動誘發旋轉失速的試驗研究 -
Nonlinear bifurcation analysis on post - stall transients of axial - flow compressor
軸流壓縮系統過失速行為的非線性分叉分析 -
3. the characteristics of boundary layer ' s transition, shape and separation are researched. the details as follows : ( l ) airfoil surface is turbulent boundary layer flows ; ( 2 ) velocity figure changed unsteady near the point of boundary layer separation due to randomicity of turbulent flow ; ( 3 ) the airfoil have better state of boundary layer separation and poor stall characteristics because of the upper surface of airfoil is flat
給出了該翼型的附面層特性：翼型表面基本為湍流附面層；在靠近附面層分離位置處，速度型形狀、特別是靠近翼型表面的底部速度型形狀變化不定，是湍流流動的隨機性所致；該翼型具有較好的附面層分離形態，但在失速迎角附近，附面層分離形態變化劇烈、失速特性差，是翼型上翼面形狀較為平坦所致。 -
Parameters influencing aerodynamic flows and transition and influence of boundary layers on outer potential flow are presented, along with associated stall and drag mechanisms
而邊界層理論受限於各種流體種類的假設，像是可壓縮性、紊流、維度和熱傳。 -
For practical purpose, an one - dimensional unsteady lumped model and a onedimensional unsteady stage - by - stage model, which are able to describe the dynamical post - stall behavior of compression systems, are derived firstly and then solved using the numerical methods to analyze the post - stall behavior and recoverability of compression systems. on the basis of characteristics of digital simulation of unsteady flow, the program for one - dimensional unsteady lumped model has compiled and tested under visual basic 6. 0 environment completely. while the program for onedimensional unsteady stage - by - stage model has compiled and tested under foitran / visual basic mixed - language environment, which part of calculation is accomplished by fortran language
根據非定常流數值模擬的特點，通過可視化編程方法，用visualbasic6 . 0編寫和調試了一維非定常總體模型的數值模擬程序；用visualbasic6 . 0製作界面，以fortran作為后臺計算程序，編寫和調試了一維非定常單元容積模型的數值模擬程序，成功地實現了vb與fortran的連接；使得數值模擬程序的界面友好，操作簡單。 -
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 -
Analysis of the effect on tip flow topologies led to some preliminary conclusions as to the flow physics involved in the stall margin improvements afforded by tip injection
通過詳細地分析頂部噴氣對壓氣機頂部區域流場結構的影響，揭示了其擴穩機理。
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