離散渦 的英文怎麼說

中文拼音 [lísǎnguō]
離散渦 英文
discrete vortex
  • 離 : Ⅰ動詞1 （離開） leave; part from; be away from; separate 2 （背離） go against 3 （缺少） dispens...
  • 散 : 散動詞1. （由聚集而分離） break up; disperse 2. （散布） distribute; disseminate; give out 3. （排除） dispel; let out
  • 渦 : 渦名詞1. （漩渦） eddy; whirlpool; vortex 2. （酒窩） dimple
  • 離散 : dispersed; scattered about; separated from one another; spread; debunching; straggling; fringing;...
  1. Eddy - current sensor conversion circuit consist amplification circuit, band - pass filter circuit, demodulation circuit, differentiation phase and data sampling circuit. these circuits are used to convert the test signal of eddy - current sensor to discrete signal tend to process. the microprocessor system that formed of dsp chip is used to data fitting of test system, data displaying and data communicating with personal computer, etc. the interference questions of hardware design and the measure of eliminating interference signal in the subject are introduced in the last of this chapter

    硬體電路的設計主要分三大部分來實現：激勵源電路部分，由分頻電路和頻率合成電路組成，產生頻率穩定的激勵信號以確保檢測任務的正常進行；傳感器變換電路部分，由放大電路、濾波電路、檢波電路、鑒相電路和數據採集電路組成，主要將電渦流傳感器檢測線圈檢測到的信號變換成只含有被測信息的離散信號，易於后續電路處理；由dsp晶元構成的微處理系統，主要完成檢測系統的數據擬合、顯示及與主機通信等功能。
  2. One cooling method that has gained increasing importance is endwall film - cooling, where coolant air is discharged though discrete holes in the inner and outer endwalls of a turbine blade passage. after leaving the holes, the coolant forms a protective layer between the hot mainstream gas and the surface that is to be protected

    目前廣泛採用的一種重要冷卻方法是渦輪葉柵端壁氣膜冷卻，該方法中冷空氣穿過渦輪葉片上內外端壁離散冷卻孔進行交換，且冷空氣流經冷卻孔后在主流熱空氣與被保護表面之間形成保護層。
  3. In the second part, firstly, the mathematical model for predicting hydrodynamic characteristics of varivec propeller under steady or unsteady condition are present, based on the general propeller lifting - surface theory, potential flow theory and green theorem. then, theoretical calculation methods for predicting hydrodynamic characteristics of varivec propeller designed above paragraphs are present, based on the finite basic solution method, the unsteady vortex lattice method and hess - smith method

    在理論計算部分，本文首先基於常規螺旋槳升力面理論、勢流理論和格林定理建立了定常和非定常狀態下全方向推進器水動力性能計算的數學模型，然後利用有限基本解法、非定常渦格法和赫斯?史密斯方法對全方向推進器定常和非定常狀態下的數學模型進行了數值離散，接下來針對前面所設計的全方位推進器進行了數值預報。
  4. 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。
  5. 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。
  6. The paper establishes mathematics model of electromagnetic heating system of eddy current field and temperature field, and gives corresponding discrete format with elements as eight nodes, hexahedron equal cell, through calculating eddy - current field to gain the internal heat source that the temperature field needed, to use discrete method to solve the problem of induction - heating part ' s temperature field by axial symmetrical electromagnetic, and then to analyze the characteristic of instantaneous temperature field

    本文建立了電磁加熱系統的渦流場和溫度場間接耦合的數學模型，分析了不同頻率下渦流和溫度的分佈情況，並以八節點六面體等參元為例給出了渦流場對應的離散格式，通過計算渦流場獲得溫度場所需要的內熱源強度，加熱部件的溫度場以軸對稱格式進行離散求解，並對瞬態溫度場有限單元法的求解特點進行了分析。
  7. ( 3 ) the most principal factors that influence the supersonic atomization process include the flow ratio of the gas - liquid metal ( gmr ) value, the flow of atomizing of gas and the range of the inverse vortex taper. the more of the value of three factors, the more advantage they are for the atomization and the more fine the powders are. ( 4 ) the produced powders are the best in efficient atomization efficiency, particle diameter, particle shape and dispersion when the solder alloy is zhl63a, atomizing medium is n2, the protrusion h = 6. 0mm, atomizing gas pressure p = 100mpa, over - heat temperature t = 167 ( t = 350 )

    研究結果表明： （ 1 ）超音速霧化器的氣體流場在導液管下端形成一個倒渦流錐，在二維空間上呈軸對稱的雙峰分佈，負壓形成於這個倒渦流錐內； （ 2 ）修正後的霧化氣體速度公式可以滿足超音速霧化的要求； （ 3 ）影響超音速霧化工藝最根本的因素有氣液質量流率比（ gmr ）的大小、霧化氣體流量和倒渦流錐范圍，三個因素的值越大，對形成細粉越有利； （ 4 ）在焊錫合金為zhl63a ，霧化介質微n _ 2 ，導液管突出高度取h = 6 . 0mm ，霧化氣體壓力取p = 1 . 0mpa ，合金過熱度取t = 167 （ t = 350 ）時，所制得的粉末在有效霧化率、顆粒球形度、粒度及其離散度三個方面綜合性能最好。
  8. 5. the numerical simulation of the axial vortex movement in the inlet side of the pump system with the method of discrete vortex provided a new way for hydromechanical characteristics of a pump system

    用離散渦方法計算渦系位置的演化模擬泵入口側渦量場的軸向渦流運動，為研究泵系統入流側渦量場特性提供了一種定量研究方法。
  9. The transient continuously distributive vortex can be replaced by a number of discrete point vortexes. the trajectory of vortex movement was computed with the method of discrete vortex and the axial vortex movement in the inlet side of the pump system was simulated

    將泵入口側連續分佈的渦量場離散成有限數目的離散渦，用離散渦方法計算渦系位置的演化，模擬泵入口渦量場的軸向渦流運動。
  10. 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
  11. Surface reconstruction is one of key techniques in reverse engineering. based on unorganized discrete points come from finite element analysis triangular mesh on exterior surface of the aeroengine hollow turbine blade, this dissertation studied some related problems, such as scattered data preprocessing, quadrangle partition and surface reconstruction technology

    曲面重構是逆向工程研究的重要內容之一，本文基於航空發動機空心渦輪葉片外表面的有限元三角網格離散點，對離散數據點的預處理、四邊域劃分及曲面重構技術進行了研究。
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