尾噴管 的英文怎麼說

中文拼音 [wěipēnguǎn]
尾噴管 英文
exhaust cone
  • 噴 : 噴動詞1. （液體等受壓力而射出） spurt; spout; gush; jet 2. （噴灑） spray; sprinkle
  • 管 : Ⅰ名詞1 （管子） pipe; tube 2 （吹奏的樂器） wind musical instrument 3 （形狀似管的電器件） valve;...
  1. Four nozzles, canted outboard, split the exhaust of the solid rocket motor into four equal tails.

    四個向外傾斜的噴管把固體火箭發動機的排氣流分成四個相等的尾巴。
  2. This engine consists of an inlet, a combustor, and a nozzle.

    這臺發動機由一個進氣道，一個燃燒室和一個尾噴管組成。
  3. Scramjet nozzle was installed at the exit of the combustor

    尾噴管直接安裝在模型發動機的燃燒室出口。
  4. In final section of this paper, the flow field of two types of supersonic nozzle for scramjet is simulated and analyzed

    最後，本文針對兩種構型的超音速尾噴管，對其流場進行了計算和分析。
  5. The effects of reynolds number, back surface of nozzle, aft - dome configuration and degree of submergence on aft - end internal flow were studied by both cold gas simulation and numerical simulation. it is showed that the separated flow is sensitive to the change of reynolds number and aft - end cavity configuration

    最後，利用冷流模擬與數值模擬相結合的方法，研究了雷諾數、噴管背壁形狀、后封頭形狀和潛入深度對燃燒室尾部流場的影響，結果表明流動的分離對雷諾數和背壁區幾何邊界的變化很敏感。
  6. In arbitrary curvilinear coordinate systems, three dimensional turbulent combustion flow fields of the three kinds of turbofan engine afterburner with the longitudinal heat shield 、 outer cold flow and the jet nozzle are simulated. the three - dimensional body - fitted grids are generated by an elliptical grid generation procedure and zone method

    本文在任意曲線坐標系統下對三種帶有縱向隔熱屏、外冷卻通道和尾噴管的渦扇發動機加力燃燒室的三維紊流燃燒流場進行數值模擬。
  7. The liner of turbine draft tube in ankang water power station was punched by cavitation, which leads to welding crack, metal shed and concrete delve, water spurting out. the cause of the damage is analyzed, the treatment is expounded

    論述了安康水電站水輪機尾水管里襯被汽蝕破壞穿透、焊縫開裂、撕裂掉塊、混凝土掏空、大量噴水的事故原因及處理方法。
  8. Abstract : the liner of turbine draft tube in ankang water power station was punched by cavitation, which leads to welding crack, metal shed and concrete delve, water spurting out. the cause of the damage is analyzed, the treatment is expounded

    文摘:論述了安康水電站水輪機尾水管里襯被汽蝕破壞穿透、焊縫開裂、撕裂掉塊、混凝土掏空、大量噴水的事故原因及處理方法。
  9. Flow details of measurement indicate that the coupling of periodic separated flow ( such as low frequency swinging of separation line ) with nozzle flow may cause aft - end internal flow unsteady. recirculation flow gains more energy from the main flow, at the same time the turbulence intensity increases

    通過對測量結果的分析，我們認為分離流動的周期性（如分離線的低頻擺動）與噴管流動相耦合，會造成燃燒室尾部流動的非穩態效應增強，增加了迴流區從主流中獲得的能量，也加劇了流場的湍流脈動。
  10. Submerged nozzles are commonly preferred in large solid rocket motors. the aft - end internal flows are very complex because of submergence. the flow process and mechanism are not very clear yet

    大型的固體火箭發動機通常採用潛入式噴管，其燃燒室尾部的流動非常復雜，流動過程及其機理尚不十分清楚。
  11. To meet the needs for wider surge margin of the turbofan engine, a new model was developed to predict the characteristics of the fan / high pressure compressor and turbine in this thesis. several ways, including, variable inlet guide vanes of the fan, variable guide vanes of the high pressure compressor, the variable inlet area ratio of the mixer and the nozzle areas, were presented to enlarge the surge margin of the turbofan engine. meanwhile, a method of combined variable geometries for optimizing controls of inlet guide vanes of the fan, guide vanes and the first two stators of high pressure compressor, area ratio of mixer and noz zle areas was established

    為了滿足下一代作戰飛機對推進系統的性能和穩定性要求，本文建立了壓縮系統特性和渦輪特性的新模型，並分別採用改變渦扇發動機風扇進口導流葉片、壓氣機導流葉片和前兩級靜葉片、混合室進口處內、外涵面積比和尾噴管面積，研究了其對發動機性能和穩定性的影響，進而得出了渦扇發動機變幾何擴穩的方法，為發動機變幾何擴穩研究打下理論基礎。
  12. Check the engine tail pipe on metal particles and visible damage

    檢查發動機尾噴管無金屬顆粒和損壞。
  13. At the preliminary stage of burning the gas flows along the back surface of the submerged nozzle and no recirculation forms in the aft - end cavity. at the medium stage of burning a weak recirculation forms in the rear of aft - end cavity by the force of injection flow. at the end stage of burning the flow separates at the c ombustion channel and a strong vortex forms in the aft - end cavity

    實驗結果表明，在發動機工作過程中隨著燃面的退移，燃燒室尾部的流動會發生很大變化，初始時刻背壁區加質流沿噴管背壁進入噴管，背壁區沒有迴流形成；中間時刻在加質流的驅動下背壁區後部形成較弱的迴流；結束時刻氣流在燃燒室壁面分離，背壁區形成強烈的迴流。
  14. The airframe and engine highly integration nature of hypersonic vehicle results in the asymmetry and cowl adjustable characters of the scramjet nozzle

    由於高超聲速飛行器機體與發動機高度一體化的構型，使超燃沖壓發動機尾噴管具有非對稱，面罩可調等特點。
  15. In this paper, experimental and computational methods were introduced to study the characters of scramjet nozzle and to guide the design

    為了解超燃沖壓發動機的工作特性，並設計其合理的構型，本文採用試驗和模擬兩種方法對超燃沖壓發動機尾噴管進行了研究。
  16. The engines would have variable nozzles, which would be fully opened on take - off and landing, so that the exhaust would be slow and relatively quiet, and narrowed when the aircraft was cruising, providing the necessary speed

    引擎將配有大小可以調節的尾噴管：起飛和降落時會全部打開，這樣噴氣速度會下降、噪音也會更小；而巡航飛行過程中，尾噴管將變小以保證必要的飛行速度。
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