氣體渦輪機 的英文怎麼說

中文拼音 [qìtǐguōlúnjī]
氣體渦輪機 英文
gas turbine
  • 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...
  • 體 : 體構詞成分。
  • 渦 : 渦名詞1. （漩渦） eddy; whirlpool; vortex 2. （酒窩） dimple
  • 輪 : Ⅰ名1 （輪子） wheel 2 （像輪子的東西） wheel like object; ring; disc 3 （輪船） steamer; steamboa...
  • 機 : machineengine
  • 氣體 : gas; gaseous fluid
  • 渦輪機 : aeroturbine
  • 渦輪 : [機械工程] turbine; worm wheel渦輪泵 [航空] turbopump; roturbo; 渦輪發動機 turbine engine; 渦輪風...
  1. Testing methods of turbo blowers and compressors for gases by loop arrangement

    渦輪式鼓風機和氣體壓縮機的封閉試驗方法
  2. Based on detailed analyze on turbine engine and ramjet, a new conceptive internal - rotor burnt rotating ramjet ( irbrr ) with an rotating cylinder in the center of rotor in which the revolved stream can be ram - compressed and burnt has been proposed and some primary research have been done as below : the scheme of structure, principles, thermodynamic cycle and performances of the new conceptive engine has been studied in the paper

    本文通過對燃氣渦輪發動機和航空沖壓發動機的原理結構進行詳細分析並進行融合創新，提出了一種利用內置旋轉汽缸進行旋轉氣流沖壓壓縮和旋流燃燒的新概念內置燃燒室旋轉沖壓發動機，並進行了一些前期的基礎性探索研究，具體研究內容有:對旋轉沖壓發動機進行了總體方案設計、工作原理分析、氣動熱力循環和性能分析等概念性研究。
  3. It is the thermal energy of the gas, after all, that the turbine converts into electricity, so the colder the gas, the lower the yield

    畢竟，渦輪機轉換成電力的能量是由氣體的熱量提供的，氣體溫度越低，發電量越小。
  4. In the matter - in - loop simulation experiment of aero - engine control system, the turbine outlet temperature, which characteristics with high and quick change, is hard to be simulated

    航空發動機控制系統半物理模擬試驗中，渦輪出口氣體溫度高、變化快，難以模擬。
  5. Guide for procurement of power station equipment. part 5 - 2 : turbines. gas turbines

    發電站設備的采購指南.第5 - 2部分:渦輪機.氣體渦輪機
  6. Test method for determination of contaminants in gas turbine and diesel engine fuel by rotating disc electrode atomic emission spectrometry

    採用旋轉圓盤電極原子發射光譜法測定氣體渦輪機和柴油機燃料雜質的試驗方法
  7. An interpolation program is used to convert the fluent result data to the ansys load data. it is a new method to analyze turbine tip clearance. in this paper, some research of the numerical computation of the tip clearance of aero - engine is done, the parametric method is used and the research on the flow, heat and structure integration analyses is accomplished

    本文對渦輪機匣氣熱固一體化分析方法做了研究，通過編制了載荷轉換與施加程序，從氣熱計算模型中提取溫度場計算結果，並作為載荷加入到熱固耦合計算模型中，實現了高壓渦輪機匣的一體化計算分析，為實現渦輪葉尖間隙的氣熱固一體化分析打下了基礎。
  8. This dissertation has on the research and design of a micro turbine engine as background and it is for the purpose of comprehending viscous flow behaviors in micro scaled conditions and that in the mini - turbine cascades. a mini wind tunnel is designed and set up which also can be used in other micro flow experiments. on the basis of this mini wind tunnel, three mini flow experiments, including micro jet experiment, micro boundary layer experiment and mini - turbine cascades experiment, have been carried out

    本文以某型微型渦輪噴氣發動機研製為背景，以認識微尺度下粘性流體流動狀態及其機理和微渦輪葉柵通道內部流動特性為目的，設計並搭建了除本實驗外還可供其他流體力學實驗使用的微型風洞，並在該微型風洞基礎上進行了微尺度射流實驗、微尺度壁面邊界層實驗和微尺度渦輪葉柵實驗。
  9. A lot of software for the measurement and control system of the codog power plant experiment rig are able to collect the status parameters of the diesel, gas turbine, gear box and electrical vortex dynamometer, to manage the data, to display, to store the data, to judge of working status and to alarm the failure

    編制了codog物理模擬實驗臺測控系統軟體，主要任務是完成柴油機、燃氣輪機、並車齒輪箱和電渦流測功器各狀態參數的採集、數據處理及顯示、數據保存、狀態判斷和故障報警等內容。
  10. 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。
  11. 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。
  12. Standard practice for design of gas turbine generator lubricating oil systems

    氣體渦輪發電機潤滑油系統設計的標準實施規范
  13. Industrial - type turbines ; steam turbines and gas expansion turbines ; construction principles for industrial - type turbines

    工業式渦輪機:蒸汽機和氣體膨脹式渦輪機:工業式渦輪
  14. 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。
  15. A temperature signal physical simulation method is proposed in this paper. the temperature simulation system is constructed and its controller is designed. the experiment results indicate that the temperature simulation system can meet the requirement of the matter - in - loop simulation of aero - engine control system

    本文提出渦輪出口氣體溫度信號的物理模擬方法，構建了溫度模擬系統，設計了溫度模擬系統控制器，進行了溫度模擬系統試驗，試驗結果表明溫度模擬系統基本滿足航空發動機控制系統半物理模擬的需求。
  16. With ms6001 gas turbine as an investigative object, an intelligent simulation and monitoring system was developed, which provides a good method to display and handle monitoring data of ms6001 gas turbine

    摘要以法國引進的ms6001燃氣輪機發電機組為研究對象，針對它開發了一套以燃氣輪機循環計算、壓氣機和渦輪特性計算及燃氣輪機變工況計算為基礎的工況監測顯示系統軟體。
分享友人
分享到 Line

分享到臉書