blade tip 中文意思是什麼

blade tip 解釋
漿葉梢部
  • blade : n 1 （殼、草等的）葉片，葉身，葉。2 刀片；（安全）剃刀刀片 （＝ razor blade）; 刀口，刃；刀，劍；...
  • tip : n 1 （塔、手指、尾巴等的）尖，尖端，頂端，末端，梢。2 裝在末端的東西，加固末端的金屬環[箍]；鞋尖...
  1. Tufted with tillers, short rhizomes and stolons ; leaf folded in bud ; leaf blade bluish green, linear with boat - shape tip ; inflorescence an open panicle ; seeds awnless. flowers from april to june

    本種?簇生形，具分? * ，亦具短的根莖及匍匐莖；葉在芽期是褶生；葉片藍綠色，長條狀，前端成船狀；花序?開放圓錐花序；種子無芒；花期4至6月。
  2. Blade thickness : 6mm at base, 5mm at tip

    刃厚：護手處6mm ，劍尖5mm
  3. In order to investigate the unsteady flow frequency domain performances of an axial flow compressor at different mass flow, rotating speed and blade row spacing, plus inlet flow distortion, and considering aerodynamic characteristics and stability of the compressor, the low speed research compressor ( lsc ) at college of energy and power in nuaa is used to carry out the experiment studies. a large amount of test data has been gained through dynamic pressure transducers embedded in the stator blades at the tip, middle and hub section, then fast fourier transform algorithm ( fft ) is applied to calculate the frequency data

    為探討軸流壓氣機在工作流量、工作轉速及動?靜葉排軸向間距變化時的葉片排流場非定常頻譜特性變化規律，並耦合進氣畸變的影響，同時與壓氣機氣動性能和氣動穩定性相關聯，作者利用南京航空航天大學能源與動力學院的低速大尺寸軸流壓氣機（ lsc ）試驗器，採取在靜子葉片表面埋入動態壓力傳感器的實驗方法，對葉尖、葉中和葉根三個截面的動態壓力進行了測量，獲得了大量的可靠的實驗數據。
  4. Finally, the experiments on the rotor bvi noise are conducted both in an aeroacoustic laboratory and at outdoors, and the noise characteristics at different locations are measured on different blade - tip mach numbers, collective pitch angles and rotor configurations. based on the experimental results, some new conclusions are presented

    本文第七章分別在「消聲室」和外場進行了模型旋翼的槳-渦干擾噪聲實驗，對不同馬赫數、不同槳距角以及不同旋翼布置情況下的不同測點進行了噪聲測量，得出了一些新的結論。
  5. He put the tip of the blade into gus's shirt and then made an arc with his arm, as though cutting a circle.

    他把尖刀伸進格斯的襯衫，隨手用胳膊劃了個弧圈，彷彿要圓圓地剮下一塊肉來。
  6. The device is used to debride polyps intranasally until normal structures can be identified. uncinectomy and maxillary meatotomy are then performed in the usual fashion, using conventional instruments. the ethmoid is entered with the tip of the blade and dissection performed posteriorly, remaining low in the ethmoid until the basal lamella is penetrated and the posterior ethmoid is entered

    通常用旋切刀來清除鼻內息肉直達正常的組織，然後用傳統器械進行鉤突切除和上頜竇竇口擴大，再用刀尖進入篩竇，向後低位切除，至穿透中鼻甲基板而進入后組篩竇。
  7. 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
  8. The result of the calculation for tip clearance is reasonable when it is compared with theory. two ways are put forward for convention of dimension of the turbine components from high temperature to low one, which is related with tip clearance, a simple example is used to illuminate that the two ways are useful, using the method of design optimization, axiisk and a blade of a certain turhine is analysed, it showes that the method of design optimization is feasible to be used for convertion of dimension of the turbine components. finally, ansys software is used to analyzed the variation of tip clearance with the method of cyclic symmetry analysis when engine works under the conditions of temperature and rotational speed, am using a new method to deal with thermal contact resistance in the calculation

    本文完善了計算渦輪葉尖間隙的簡化演算法程序，增加了程序的計算功能，並將其應用於某高壓渦輪進行葉尖間隙分析，所得結果與理論結果進行了對比，得出修改後的程序用於葉尖間隙計算是合理的；同時提出了與葉尖間隙相關的渦輪典型部件的冷、熱態的尺寸兩種換算方法，使用優化設計的方法進行了實例分析，說明了所提出的計算方法是可行的；最後應用ansys有限元軟體利用循環對稱的方法分析了某型發動機高壓渦輪在溫度場及離心力作用下的葉尖間隙在發動機工作過程中變化情況，並分析了計算中的接觸熱阻的處理問題。
  9. The two edges were formed in apple seed shape to give a strong support during blade contacts, while the edges near the tip area transformed smoothly into flat grind to give supreme sharpness to the delicate cuts that characterized chinese swordsmanship

    而靠近劍尖處的鋒口則流暢地轉化成更為鋒利的平面式開鋒，讓中國劍法里著名的點和割等小巧切割動作得以全面發揮。
  10. 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。
  11. At the same time, tip leakage induced by pressure gradient and relative motion between the blade tip and the shroud wall is found to have a major influence on detailed flow properties in tip region of rotor passage

    同時，由於轉子葉片壓力面和吸力面之間壓力梯度以及葉頂與機匣之問的相對運動產生的間隙流對轉子通道內的細微流動結構有較大的影響。
  12. 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。
  13. Experimental study on film cooling at rotating flat blade tip

    旋轉平板型葉端氣膜冷卻實驗研究
  14. 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。
  15. 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。
  16. Abstract : a 3d numerical solution of transonic turbulent flowfield inside a compressor rotor is analyzed with a consideration of blade tip clearance

    文摘:藉助于考慮葉片頂部間隙的壓氣機轉子內跨音速湍流流場的三維數值解，得到了該轉子流場中的復雜渦系與波系結構。
  17. Development of rotating linear cascade facility for simulating blade tip clearance flow

    模擬葉尖間隙流的轉動平面葉柵實驗方案
  18. Blade tip clearance

    葉尖與船體的間隙
  19. 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
  20. 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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