氣冷葉片 的英文怎麼說

中文拼音 [qìlěngyèpiān]
氣冷葉片 英文
air-cooled turbine blade
  • 氣 : Ⅰ名詞1 （氣體） gas 2 （空氣） air 3 （氣息） breath 4 （自然界冷熱陰晴等現象） weather 5 （氣味...
  • 冷 : Ⅰ形容詞1 （溫度低; 感覺溫度低） cold:冷水 coldwater; 你冷不冷? do you feel cold?; are you feeling...
  • 片 : 片構詞成分。
  1. 4 heating zones on barrel, all with air - cooling. each zone with multiple rows of copper fins for high cooling efficiency, coupled with oversized cooling fans mounted at the rear of the extruder barrel. large wattage on heaters coupled with the efficient cooling system ensures very fast heating and cooling of each zone

    機筒上有4個加熱區域，都帶有空氣冷卻裝置；每個區域含附帶大冷卻風扇的多排銅葉片可獲得高冷卻效果，高功率的加熱模塊同有效的冷卻系統相結合可以確保每個區域的快速加熱和冷卻。
  2. 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
  3. 4 ) in a pre - swirl rotator - stator cavities with discrete pre - swirl nozzles and blade - cooling entry holes, the influences of pre - swirl angle and flow parameter on the flow and heat transfer characteristics were numerically investigated. the correlation for average nusselt number vs rotating reynold number or non - dimensional mass flowrate were established. the results show that : advantage of per - swirl inflow is the effect of cooling the blade - cooling entry holes ; pre - swirl inflow increases heat transfer in rotating disk of pre - swirl chamber ; as pre - swirl angle increases, local nusselt number decreases in pre - swirl chamber ; the temperature of stator of inner rotator - stator chamber and per - swirl chamber decreases as rotating reynold number increases ; when the axial mass flowrate maintains constant, heat transfer in the rotating disk of inner rotator - stator cavities does n ' t change as per - swirl mass flowrate increases, while heat transfer in the rotating disk of per - swirl chamber increases ; when the pre - swirl mass flowrate maintains constant, change of the axial mass flowrate has effect on the whole cavity

    結果表明，預旋進氣的優點在於增強了葉片冷卻孔附近的對流換熱效果，局部努謝爾數隨預旋角的增大而有所減小；隨旋轉雷諾數的增加，不論是內轉靜腔室還是預旋腔室的靜盤上的溫度都不同程度的降低：當軸向中心進氣質量流量不變時，隨預旋進氣的質量流量增加，內轉靜腔室的轉盤盤面上的換熱基本沒有變化，而預旋腔室的轉盤盤面上的換熱效果增強；當預旋進氣質量流量不變時，軸向中心進氣的質量流量的改變對整個盤腔都有影響。
  4. 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。
  5. The blade inner channel cooling is a complex convection - conduction coupling problem. this thesis build a three - dimension. compressible turbulence model, and give a general solve method. with the geometrical model of the glossily rectangle straight channel, the rectangle straight channel with in - line arrays disturb plates, the rectangle straight channel with staggered arrays disturb plates, the rectangle straight channel with slant disturb plates, this thesis compute the flow and heat transfer condition when the cold air path though these channels, and gain the temperature field, pressure field, velocity filed, in addition. this thesis also analyze the influence of the different channel height, the different channel materials, the different channels, and gain the function relation between he nusselt number, friction factor and reynolds number. this thesis is emphasis on the new heat transfer enhancement structure, that is, disturb plates, with the comparison with the glossily channel and channel with pin fins, the heat transfer enhancement effect of the former is better, and the conclusion can be used in the design of aircraft blade

    葉片內部通道冷卻是一個復雜的對流?導熱耦合傳熱問題，本文在分析葉片內部通道冷卻的流動與傳熱情況的基礎上，建立了三維、可壓縮紊流的物理模型，得到了通用的求解辦法；利用不帶擾流片的矩形直通道、帶順排擾流片矩形直通道、帶叉排擾流片、帶傾斜擾流片的矩形直通道的幾何模型，計算了冷卻空氣通過這幾種通道時的流動與換熱情況，得到了各種不同情況下計算區域的溫度場、壓力場、速度場；在此基礎上分析了不同的通道高度、不同的葉片通道材質對葉片內部通道冷卻的影響，並整理得到了各種通道形式下，努謝爾數和阻力因子與雷諾數的函數關系；本文重點研究了新型的葉片內部通道冷卻強化傳熱措施?帶擾流片的內部冷卻通道的強化傳熱效果，通過與光滑矩形直通道、帶針肋通道的冷卻效果的比較，表明了這種新型鮚構的優勢，對于葉片內部通道冷卻結構的設計可以起到指導的作用。
  6. ( 2 ) on the leading edge, the film cooling effectiveness at the zone immediately downstream of the cooling holes is affected by blowing ratio and mainstream reynolds number, while the effects are not important in the downstream zone far from the cooling holes. ( 3 ) on the front half of pressure surface, the effectiveness increases with decreasing blowing ratio at the downstream near the cooling row and it is contrary at the downstream far from the cooling row. ( 4 ) on the rear pare of the pressure surface, the effectiveness decreases with increasing blowing ratio and does not vary so much downstream in the cases of higher blowing ratio

    研究結果表明葉片吸力面端壁附近區域壓力系數分佈呈現出較強的三維特性，動葉吸力面尤其明顯；氣膜孔流量系數隨吹風比的增加而增大，在高吹風比情況下，流量系數逐漸趨于常數；在不同型面區域，冷卻效率分佈有較大的差異，而且吹風比與主流雷諾數的影響程度也不盡相同；低吹風比下，孔出口下游附近可以得到較好的冷卻，中、高吹風比下，冷氣射流在加速流動主流的作用下返回壁面進行二次冷卻，孔下游較遠區域可以得到較好的冷氣覆蓋。
  7. A new model for film cooling effectiveness computation on blade surface in a turbine cascade

    渦輪葉片型面氣膜冷卻效率的計算模型
  8. Touch on developing large - flow and high - pressure ratio impressor and large - enthalpy drop turbine, reducing harmful emission, solving the major problems of high - temperature blade material, cooling, protective coating and single - grain blade casting, and comfirm some important manufacturing techniques

    涉及了開發大流量高壓比壓氣機、大焓降渦輪，降低有害排放量，解決高溫葉片的材料、冷卻、保護塗層及單晶葉片鑄造等主要問題，並確認了一些關鍵的製造技術。
  9. Phenomena, such as flow field confusion and slagging etc. have occurred in the practical process of cyclone burner for coal - water slurry ( cws ) firing, on this basis a study on aerodynamic field of cws cyclone burners had been carried out through cold state experiments in the laboratory, then the influence of burner ' s structure properties upon the said flow field had been carried out, and expected to find more reasonable structure of the burner was found. in my study the focus is on the affection of cone and cyclone intensity in the condition of infinite and finite fields

    本文著重研究現有水煤漿旋流燃燒器的旋流葉片角度，一次風擴口的長度以及角度對旋流燃燒器出口流場的影響，通過流場的比較，以期得到性能較好的旋流燃燒器。考慮到水煤漿燃燒器中心的水煤漿射流對于其空氣動力場的影響，本文在實驗室冷態實驗研究的基礎上，模擬水煤漿射流，研究其對燃燒器空氣動力場的影響。
  10. 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。
  11. 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。
  12. Measured hole mass flows and a constant static pressure mixing analysis, together with the measured losses, allowed the decomposition of the losses into three distinct entropy generation mechanisms : loss generation within the hole, loss generation due to the mixing of the coolant with the mainstream, and change in secondary loss generation in the " blade passage

    論文還進行了葉片冷卻孔質量流的測量與常靜壓氣流混合分析，結合前述氣動力損失和冷卻空氣損耗的測量結果表明，端壁氣膜冷卻的綜合損失明顯地由三個部分組成：葉片冷卻孔內產生的損失；由於冷卻空氣與主流熱空氣的混合產生的損失；二次流的變化產生的損失。
  13. The experimental results showed that the film cooling effectiveness were mainly determined by blowing ratios

    該實驗結果對渦輪葉片型面氣膜冷卻的實際工程設計研究有重要意義。
  14. To compare with great deal of experimental data, the results show the improved method could be used as a generalized design methodology of film cooling for turbine blade. predictions of span - wise averaged effectiveness are made with a two - dimensional boundary layer code using the low reynolds number k - two - equation turbulent model

    研究並發展了用低雷諾數k -紊流模型為基礎的氣膜冷卻計算方法，將前人針對平板提出的摻混模型推廣應用於渦輪葉片型面，得到了與實驗數據符合良好的結果。
  15. 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。
  16. Abstract : by using 2 - d finite element method ( fem ) and experiment, the phenomenon of heat conduction in tc11 ti alloy compressor blade is simulated and analyzed during the post - forge cooling course, and the time _ variation characters and distribution laws of transient temperature fields of every airfoil section are obtained

    文摘:運用二維有限元法和試驗方法，模擬、分析了tc11鈦合金壓氣機葉片鍛后冷卻過程的傳熱現象，得到該葉片各個翼形截面上瞬態溫度場的時變特性和分佈規律。
  17. 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。
  18. Film cooling of the surface of a gas turbine blade was studied in a large - scale low - speed opening wind tunnel according to actual requirement of the design of aero - engine. the surface of a gas turbine blade was cooled by cylindrical holes in the experiment, with the hole number of fifteen in stator and eight in rotor

    應航空發動機設計的要求，在大尺寸低速葉柵傳熱風洞中分別對發動機渦輪導向葉片和動葉表面的氣膜冷卻特性進行了研究，具體研究在不同氣膜孔出流時，在不同主流雷諾數和吹風比情況下葉片表面局部換熱系數的分佈規律。
  19. 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。
  20. Since it is the first use of the momentum - blade theory to predict cooling fan aerodynamic performance, the work presented in this paper is still open for further investigation

    但由於本文使用的將動量?葉素理論運用到汽車冷卻風扇這種小展弦比的葉片的氣動計算上，尚屬首次，對于結果中存在的偏差的確切原因，尚有待于在今後的工作中繼續研究。
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