blade vortex 中文意思是什麼
blade vortex
解釋
葉片渦流-
The research on the rotor blade - vortex interaction ( bvi ) noise is a very important aspect and a very challenging subject in the rotorcraft aeroacoustics field
旋翼槳-渦干擾噪聲問題是直升機氣動聲學領域的一個研究熱點和難點。 -
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 main research outcomes were as follows : ( 1 ) the paper applied quasi - three dimensional design model and optimization design model based on si flow surface that was effected by runner ( impeller ) and guide vane jointly. the vortex flow, blade thickness limitation and runner ( impeller ) blade force functions were taken into account. the paper got the improved runners of hl240 type, which were runner hlx240d and runner hlx240e
主要成果有： （ 1 ）應用考慮轉輪來流有旋、葉片有限厚及轉輪（葉輪）葉片力作用的轉輪（葉輪）與導葉聯合作用的基於s _ 1流面的準三維設計模型和優化設計模型，研究出了hl240的改進型轉輪： hlx240d和hlx240e 。 -
Based on the green ' s formula and the assumption of the propeller blade ' s thin sections, a lifting - surface method of propellers with the vortex lattice and equal source panel distributions on the mean camber surface has been introduced for the prediction of steady propeller ' s hydrodynamics in this paper. an approximate kurta condition was applied
基於creen公式和薄翼理論假設導出的升力面方法，採用在螺旋槳拱弧面上分佈離散渦、源布置方法預報均勻流場中的螺旋槳的定常性能，螺旋槳尾渦面上壓力連續性條件採用近似的kutta條件處理。 -
The surface of propeller, hub and the vortex of blade is discreted by a number of small hyperboloidal quadrilateral panels with constant source and doublet distribution
槳葉、槳轂表面和螺旋槳尾渦面採用四邊形雙曲面元離散，以消除面元間的間隙。 -
Abstract : this paper uses the topology theory to analyze the surface flow spectrums of straight, positively curved and negatively curved cascades with relative tip clearances of 0. 023 and 0. 036, finds apparent differences of topology and vortex structures in the blade tip and the suction side wall corner of single type of cascade with this two clearances, and studies the mechanism of the difference formation as well as their effects on the energy loss
文摘:應用拓撲原理分析了葉頂相對間隙為0 . 023和0 . 036的渦輪直葉柵和正、反彎葉柵的壁面流譜，發現在兩種間隙下同類葉柵的拓撲與旋渦結構在葉頂和吸力面壁角明顯不同，探討了差別形成的機理及其對能量損失的影響 -
In this paper, the contents and the methods of the impacting test to the particle separator vortex blades by the foreign object are introduced, the ultra dynamic strain device is used to carry on the measure of this experiment and obtained the strain - time history, three dimensional coordinate measuring method is used to measure the remaining distortion of the vortex blade, and the high speed photographic apparatus is used to carry on the photography of the impacting experiment
本文介紹了對粒子分離器渦流葉片進行外物撞擊試驗的內容和方法，採用超動態應變儀對外物撞擊試驗進行了測量，獲得了渦流葉片不同外物撞擊下的應變-時間歷程，採用三坐標法測量了外物撞擊后渦流葉片的殘余變形，並採用高速攝影儀對外物撞擊渦流葉片的全過程進行了拍攝。 -
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 numerical simulation and experimental research made on the characteristics of the clearance cavitations in kaplan turbine are described herein ; in which the analysis mainly is concentrated on the characteristics of leakage - vortex caused by the flow of the clearance between blade tip and blade chamber, that occurs at the front - pressure side of the blade, and the intensity of the secondary - flow - vortex ; furthermore, the relationship in between the leakage - vortex, secondary flow vortex, cavitations and erosion are analyzed as well
摘要對軸流轉槳式水輪機輪緣間隙流動及空化特性進行數值模擬和試驗研究，重點分析輪緣間隙流動在正面頭部泄漏流動所引起的泄漏渦帶、二次流動的漩渦強度和空化特性，以及泄漏渦帶旋轉、二次流動的漩渦與空蝕和磨損之間的關系。 -
The surface panel method has been applied to predict the hydrodynamic performance of highly skewed propeller. the surface of propeller and its trailing vortex are discreted by a number of small hyperboloidal quadrilateral panels with constant source and doublet distribution. for highly skewed propeller, the conventional method generating grid oriented along constant radii will result in a high aspect ratio and a high skewness and a twist panel near the propeller tip on blade surface, which result easily in incorrect calculation results of velovity on blade surface, even in iteration divergence and calculation failure. a “ non - conventional grid ” is developed to acoid these problems. this grid can effectively solve the problem of the calculation and convergence for highly skewed propeller. the non - linear kutta condition of equal pressure on upper and lower at the trailing edge is executed by the iterative procedure. by sample calculating, the obtained results are satisfied the experimental data
採用面元法預報大側斜螺旋槳水動力性能，螺旋槳表面及尾渦面離散為四邊形雙曲面元，每個面元上布置等強度源匯和偶極子分佈.對于大側斜螺旋槳而言，槳葉表面採用常規的等半徑網格劃分方法在近葉梢處將導致大展弦比、大側斜和扭曲面元，這容易使槳葉表面速度的計算結果不正確，甚至會導致迭代過程發散及計算失敗.文中建立了一種「非常規網格」劃分方法，能有效地解決大側斜螺旋槳的計算和收斂問題.槳葉隨邊處通過迭代實現非線性等壓庫塔條件 -
In lifting - surface theory, the non - liner phenomena of the trailing vortex in the transition wake area and of the tip vortex separation are considered. in surface panel method hyperboloidal quadrilateral panels are employed and the morino ' s analytical formulation is used to determine the influence coefficients. the more reasonable pressure kutta condition is satisfied at the trailing edge of propeller blade
在計算中，對于升力面理論，本論文考慮了過渡區尾渦收縮和葉梢分離的非線型現象的影響；對于面元法，本論文採用的是計算較為簡便的基於擾動速度勢的基本公式及雙曲面形狀的面元，在槳葉隨邊滿足更趨合理的壓力kutta條件，並用morino導出的解析公式計算面元的影響系數的快速有效的數值預報方法。 -
Therefore, it is important to know about the damage rule of particle separator, to analyze the degree of blade distortion by means of tests and calculations, to propose a set of vortex blade anti - impact ability appraisal methods
因此，了解外物對渦流葉片的損傷規律，通過試驗和計算手段來分析葉片變形、產生裂紋或缺損的大小和程度，提出一套渦流葉片抗外物損傷能力的評估方法，對于粒子分離器的抗外物損傷設計是非常有必要的。 -
On the basis of the impacting test of particle separator vortex blade, utilize ansys / ls - dyna finite element software to carry on the value computation to the impacting process and the analysis to the computed result ; and carry on the comparison to the computed result and the test result, two kind of results tally well
在粒子分離器渦流葉片外物撞擊試驗的基礎上，運用ansys / ls - dyna有限元軟體對撞擊過程進行了數值計算，對計算結果進行了分析;並對計算結果和試驗結果進行了比較，兩種結果吻合較好。本文開展的對粒子分離器渦流葉片的外物撞擊試驗和數值計算，在國內屬首次進行。 -
The particle separator ( ips ) is a special device of helicopter used for the purification of the entrance air and the protection of the engine. the vortex blade of the particle separator will be damaged if impacted by the foreign object for a long time, thus the separation efficiency of the particle separator and the safety of the engine will be affected
粒子分離器是直升機上用來對發動機進行進氣凈化和防護的一種專門裝置，外來物的撞擊會對粒子分離器的渦流葉片造成損傷，影響粒子分離器的分離效率，從而對發動機安全帶來影響。 -
The analytical and experimental system for the responses of vortex blade under the impact, which can be used in the anti - impact design of vortex blade, is established in the research work of this paper
在本次研究工作中建立的渦流葉片外物撞擊瞬態響應分析系統，可供渦流葉片抗外物損傷設計時應用。 -
A new aerodynamic design system developed by authors for draft fan with enhanced efficiency, suppressed noise, enlarged flux and high load. the new design system features : a twist regulation for vortex control is employed in designing to lessen the secondary flow loss in the blade tip and hub ; the feasibility and high efficiency of this procedure has been verified by the tests of the prototype fan ; a new computer - aided 3d blading is used to optimize the blade ; numerical inverse checking is adopted to enhance accuracy in designing and cut down the period of the designing and production. this design system can make the optimized blade with " forward inclination ", " inclining sweep ", " bending sweep ", to minimize the various secondary flow losses, to expand the steady working range of the fan, and to suppress the aerodynamic noise source
本文通過對一種新型高性能礦用局部通風機的設計、製造及試驗全過程的綜述，展現了新的先進設計體系在民用通風機上的成功運用，其研製特點是： （ 1 ）在葉片氣動設計中為了降低葉根及葉尖區二次流損失，採用可控渦扭向規律設計，樣機實測的高性能驗證了這種方法的可行性和高效性； （ 2 ）在設計方法中採用較精確的數值反驗算，獲取最優設計方案，大大提高設計的準確性和成功率，並縮短了設計試制周期； （ 3 ）在設計過程中發展了計算機輔助三維葉片造型新方法，可以根據設計需要簡便快捷地對葉片進行「前傾」 、 「傾掠」或「彎掠」造型，這些造型對減小各種二次流損失、擴大穩定工況范圍和控制葉輪機氣動噪聲源起到了非常好的作用。 -
Abstract : a new aerodynamic design system developed by authors for draft fan with enhanced efficiency, suppressed noise, enlarged flux and high load. the new design system features : a twist regulation for vortex control is employed in designing to lessen the secondary flow loss in the blade tip and hub ; the feasibility and high efficiency of this procedure has been verified by the tests of the prototype fan ; a new computer - aided 3d blading is used to optimize the blade ; numerical inverse checking is adopted to enhance accuracy in designing and cut down the period of the designing and production. this design system can make the optimized blade with " forward inclination ", " inclining sweep ", " bending sweep ", to minimize the various secondary flow losses, to expand the steady working range of the fan, and to suppress the aerodynamic noise source
文摘:本文通過對一種新型高性能礦用局部通風機的設計、製造及試驗全過程的綜述，展現了新的先進設計體系在民用通風機上的成功運用，其研製特點是： （ 1 ）在葉片氣動設計中為了降低葉根及葉尖區二次流損失，採用可控渦扭向規律設計，樣機實測的高性能驗證了這種方法的可行性和高效性； （ 2 ）在設計方法中採用較精確的數值反驗算，獲取最優設計方案，大大提高設計的準確性和成功率，並縮短了設計試制周期； （ 3 ）在設計過程中發展了計算機輔助三維葉片造型新方法，可以根據設計需要簡便快捷地對葉片進行「前傾」 、 「傾掠」或「彎掠」造型，這些造型對減小各種二次流損失、擴大穩定工況范圍和控制葉輪機氣動噪聲源起到了非常好的作用。 -
In chapter 6, a new idea for simulating rotor bvi noise experiment is presented using a scissors rotor configuration with the vertical separation between a pair of rotors, based upon the fact that the important aerodynamic feature of this scissors rotor configuration is its close blade - vortex encounter. and the models and facilities designed for the bvi noise experiment are given
在第六章，基於槳-渦靠近通過是非共面剪刀式布置旋翼流場的一個重要特徵，提出了使用剪刀式布置旋翼來模擬旋翼槳-渦干擾噪聲實驗的新構想，並設計了用於噪聲實驗的模型。 -
There were some intensively nonlinear features in the vibrating cascade flow. the frequency of the separated vortex ' s propagation was not equal to the vibrating frequency of the blade
二維分析中發現振動葉柵非定常粘性流動具有較強的非線性特徵，振動誘發的分離渦傳播頻率與葉片的振動頻率不一致。 -
Finally, multi - passage method was adopted to deal with the phase - difference periodic boundary condition. when the frequency of separated vortex propagating is not the same as the vibrating frequency of blade, this method is much more reasonable than those simple phase - shifted periodic condition in single passage
最後，採用多葉柵通道計算來處理相差周期邊界條件，在分離渦傳播頻率與振動頻率不同時比其它採用簡單相移條件的方法更為合理。
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