high-area-ratio nozzle 中文意思是什麼

high-area-ratio nozzle 解釋
大面積比噴管
  • high : adj 1 高的〈指物，形容人的身高用 tall〉；高處的；高地的。2 高級的，高等的，高位的，重要的。3 高尚...
  • area : n. 1. 面積；平地；地面。2. 空地；〈英國〉地下室前的空地。3. 地區，地方；〈比喻〉區域；范圍。
  • ratio : n. （pl. ratios）1. 比，比率，比值；比例；系數。2. 【經濟學】復本位制中金銀的法定比價。vt. 1. 用比例方式表達；求出…的比值；使…成比例。2. 將（相片）按比例放大或縮小。
  • nozzle : n. 管嘴；噴嘴；〈俚語〉鼻子。 a jet [propelling] nozzle 【火箭】尾噴管。
  1. The ratio of the diameter of nozzle to the diameter of vessel has greater effect on the distribution area of high stress in plastic deformation stage

    對于均處于塑性階段的結構而言，開孔率的大小對高應力區的分佈范圍影響較大。
  2. These variable geometry components include high pressure - compressor, high - pressure turbine, low - pressure turbine, inlet area ratio of mixer and main nozzle throat area. the results of calculation show that the adjusting of low - pressure turbine and mixer has a remarkable effect on the performance of engine and bypass ratio

    計算結果表明，低壓渦輪和混合器的調節對發動機的性能和涵道比的影響尤為顯著；在其它部件幾何結構不同時，單個部件幾何調節后，發動機性能的變化趨勢是不同的。
  3. 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。
  4. ( 3 ) on the background of the development of an ignition rocket, some application investigations have been carried out. some parameters related to water - resistant ignition mixture, the charge of ignition rocket, such as heat - flow, density of charges, structure of charges, coating and its process, area ratio of nozzle and high temperature corrosion of the nozzle, were calculated and studied, respectively. on the basis of the above studies, an ignition rocket was successfully developed

    （ 3 ）進行了應用研究，以某系列點火發動機的研製為背景，分別對耐水點火藥用作點火發動機裝藥所涉及的能量衡算、裝藥密度、裝藥結構、包覆及其工藝、喉面比及噴口燒蝕等問題進行了分析和實驗研究，在這些研究的基礎上成功地製作了一種點火發動機。
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