blades cooling 中文意思是什麼
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When the equipment is wirking, the blades will be nipped on the table. after the blades is faced with table side face, the workstations can be transferred to any angle. milled into an any angle blade, automatic lubrication, automatic cooling, especially for the aerodynamic drawknife blades
本機在工作時，將刀片夾在工作臺上，刀刃與工作臺的側面面對齊壓緊后，可以將工作臺轉至任何角度，磨成任意角度的刀刃，自動潤滑，自動冷卻，適應于不同厚度，不同規格的刀片，成其適合於氣動刮刀刀片面性的研磨。 -
Numerical simulation of leading edge film - cooling of turbine stator blades
氣膜冷卻渦輪導向葉片流場數值模擬 -
The welding technology of francis turbine runners is optimized from the view of subsection welding and local heating by numerical simulation. the result shows that welding residual tensile stress appears in the weld and its area nearby, and peak stress appears in the dangerous area of blades after practising quondam welding technology ; welding residual tensile peak stress in the dangerous area of blades can be decreased by welding both ends earlier and then welding middle section later during subsection welding, and decreasing effect on welding residual stress of the subsection welding is related to the weld length of blade outlets and welding direction of each subsection ; decreasing effect on residual stress of the local heating is direct proportional to heating time, heating temperature, heating area, and inversely proportional to cooling area, and welding residual tensile peak stress in the dangerous area is decreasing trend earlier, and then increasing trend later with heated location increased
本文利用數值模擬手段對轉輪的焊接工藝從分段焊和局部加熱兩個方面進行了優化，結果表明:採用普通工藝焊接時，葉片焊后殘余拉應力出現在焊縫及其附近區域，並且在葉片出水邊的熔合線附近（危險區域）出現了峰值;在採用優化的分段焊時，先焊兩端后焊中間的方法可以降低葉片危險區域的焊接殘余拉應力峰值，降低效果與葉片出水邊焊段長度、焊縫各段的焊接方向有關;局部加熱法降低轉輪危險區域殘余應力的效果主要與加熱時間、加熱溫度以及加熱面積成正比，與冷卻面積成反比，並且危險區域的殘余應力隨加熱區域的增大呈先降低后升高的趨勢。 -
In this paper. the conclusion of this paper has utility meaning in analysis on turbine blades cooling after some proper correcting of the geometry structure and boundary conditions
由於所採用的結構及計算域近似渦輪葉片的冷卻形式（主流加熱，內流通道冷卻） ，因此這種方法經過進一步的改進，可用於渦輪葉片冷卻的計算研究。 -
Clogging up of the cooling air slits in the turbine blades is primarily caused by ultrafine particles with a high specific surface area
渦輪葉片之間冷卻空氣縫隙的堵塞主要是因為存在高比表面積的超細粒子。 -
Numerical simulation of the impact of leading - edge gas - film pores on cooling effectiveness in turbine stator blades
前緣氣膜孔對渦輪靜葉冷卻效果影響的數值模擬 -
The paper analyze the limitations of serial gas turbine model, take single axis gas turbine as prototype, with the intensive analyzes and profound of the principles and characteristic of the object, using the modular modeling method proposed the dynamic model of gas turbine, which including the model of compressor, combustor, turbine. with respect to the purposes and key points of establishing model, the model is simplified. the intensive cooling of turbine blades is also modeled
在建模過程中，結合本文建模的目的和重點，對原型作了合理的簡化，考慮了壓氣機抽氣對透平葉片的冷卻，對壓氣機和燃氣透平按級進行分析和處理，採用模塊化建模的方法分別建立了燃氣輪機主要部件壓氣機、燃燒室、燃氣透平的動態數學模型，所建模型比集總參數模型具有更好的精確性。 -
On optimizing pin - fin shape for efficient cooling of turbine blades
層板發汗冷卻推力室的傳熱特性 -
But the outer wall of the turbine blades was washed by high temperature gas, the internal passage was cooled by cooling gas which was induced from the compressor
而渦輪葉片的特點是外部受高溫燃氣的沖刷，內部通道通過從壓氣機引來的冷氣進行冷卻。 -
Comprehensive understanding of how the rib geometries affect the discharge coefficients of the film holes and how the holes " extractions affect the pressure losses of the passage, would allow designers to optimize the layout of the internal cooling passages of the blades for acquiring higher cooling performances
為詳細了解此種通道中的肋對氣膜孔出流特性的影響以及氣膜孔出流對通道流阻特性的影響，本文採用了實驗和數值模擬相結合的方法進行了系統的研究。 -
Some of the air is used for cooling the turbine blades and nozzle guide vanes, and part of it is employed to cool and seal the turbine discs
在現代航空發動機中，從壓氣機引出的壓縮空氣一部分用來冷卻渦輪葉片和渦輪導向葉片，另外一部分用來冷卻和密封渦輪盤。 -
To satisfy the practical need of film cooling in turbine blades of aeroengine, some detailed experimental measurements on the flow field in the channel with the holes on the wall and in the holes had been completed within a wide range of aerodynamic parameters. and the interrelated numerical simulated compute had also been implemented
本文根據航空發動機中渦輪導向葉片氣膜冷卻的實際需要，在寬廣的氣流流動參數范圍內，對葉片內冷通道的流場進行了詳細的實驗測試，同時還進行了相應的數值模擬計算。
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