進氣道進口 的英文怎麼說

中文拼音 [jìnqìdàojìnkǒu]
進氣道進口 英文
approach of entry
  • 進 : 進構詞成分。
  • 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...
  • 道 : Ⅰ名詞（道路） road; way; route; path 2 （水流通過的途徑） channel; course 3 （方向; 方法; 道理） ...
  • 口 : Ⅰ名詞1 （人或動物進飲食的器官; 嘴） mouth 2 （容器通外面的地方） mouth; rim 3 （出入通過的地方） ...
  • 氣道 : air flue; air passage
  • 進口 : 1 （船隻進港） enter port; sail into a port2 （外貿進口） import3 （入口） entrance; [機械工程] i...
  1. The anchor flange for west - fast gas pipeline project is a kind of important device to avoid axile thrust damages all valve of electric field and the anchor flange of the project are only supplied by my company. the anchor flange has replaced import product, filling up domestic blank and achieving nationalization.

    錨固法蘭是西氣東輸管道工程為防止軸向推力對各種站場閥室造成破壞而設置的一種重要裝置。全線所用的錨固法蘭均由我公司獨家供應。該產品代替了進口，填補了國內空白，實現了國產化。
  2. The effect of exit back pressure and length / height ratio of isolator on forebody / inlet flow field is analyzed and discussed in the paper

    本文還研究了隔離段出口反壓及隔離段長高比對進氣道流場的影響。
  3. With account for the effect of temperature and shock - boundary layer interaction, the forebody / inlet with plane lip and wedge lip are designed by using the design methods of constant shock wave intensity and constant shock wave angle. in the design, the incidence angle of the first ramp, height of isolator, length of forebody and total turning angle of the designed forebody / inlet models are given

    另外，根據優選結果，給定前體長度、前體預壓縮楔角、總壓縮轉角及隔離段高度，分別用等激波強度和等激波角度的方法設計了唇口平直和唇口帶楔角的前體進氣道。
  4. The calculation results indicate that the starting performance of forebody / inlet with wedge - shaped lip is better than that with plane lip at low flight mach number. at high flight mach number, the performance of the forebody / inlets designed by the two methods is approximate. at low flight mach number, the starting performance of forebody / inlet designed by the method of constant shock wave intensity is better

    結果表明：唇口帶楔角的進氣道在低飛行馬赫數下的起動性能優于唇口平直的進氣道；採用等激波強度和等激波角度方法設計的進氣道在高飛行馬赫數下的性能相近，在低飛行馬赫數下，採用等激波強度方法設計的進氣道起動性能較優。
  5. Reynolds numbers ( based on average velocity at passage inlet and hydraulic diameter of the passage ) are changing from 20000 to 80000 and the extraction ratios ( suction ratios, sr ) are changing from 0. 30 to 0. 60 for each test model. so the influences of reynolds numbers, suction ratios and etc. on the discharge coefficients and pressure loss characterist ics are also presented. flow fields of typical passages are visualized with the flow visualization techniques and measured with hot - wire anemometer

    對每一種通道結構，實驗在不同通道進口雷諾數（ re = 20000 、 40000 、 60000 、 80000 ）和不同通道總出流比（ sr = 0 . 30 、 0 . 45 、 0 . 60 ）下進行，以研究這兩個流動參數及其它相應變化的參數（氣膜孔的雷諾數re _ h 、氣膜孔與通道的動量比i等）對出流特性和流阻特性的影響規律。
  6. Low - level windshear and turbulence alerts for the approach and departure areas within 3 nautical miles of the runway thresholds are issued by the amo for relay by air traffic controllers to approaching and departing aircraft

    機場氣象所發出在跑道進口3海里內的機場升降區的低空風切變及湍流警報，由航空交通管制員轉送至正在升降的航機。
  7. The results prove that : ( 1 ) when the mach number of the flow at the exit increases, the total pressure recovery decreases, and the circular steady total pressure distortion coefficient, turbulence intensity and synthesis distortion increase

    研究結果表明： （ 1 ）地面工作狀態下，隨著出口馬赫數的增加，蛇形進氣道出口截面的總壓恢復系數不斷下降，而穩態周向畸變指數、紊流度和綜合畸變指數均上升，穩態徑向畸變指數變化不大。
  8. Finally, the inlet port and combustion chamber designed and machined is tested on 4100qb. the paper mostly investigates the change of performance targets of the engine that three different grooved chambers including two different re - entrant model and one w model match with various intake port and nozzles, in order to realize the influence of chamber geometry on combustion process. the results analyzed have indicated that re - entrant grooved chambers can enhance the turbulent intension in the chamber, improve the combustion proces of diesel engine on the altiplano, being groove, re - entrant and convex, and have the farther developing potential

    著重研究兩種縮口、一種直口矩形環槽燃燒室與不同進氣道、噴油嘴的組合方案發動機的動力性、經濟性及排放指標的變化，確定燃燒室的幾何形狀對燃燒過程的影響。分析結果表明，由於有矩形環槽、燃燒室縮口以及燃燒室底部凸臺，縮口矩形環槽燃燒室中的紊流得以加強，改善了高原柴油機的燃燒過程，這種燃燒室有進一步發展的潛力。
  9. A parametric analysis of the inviscid effects of leading edge sweep, sidewall compression, width - height ratio, cowl position and inflow mach number on spillage is finished. numerical simulations are completed for a series of inlets at various flight height and velocity. the research indicates that the area of spillage window, which is mainly determined by the position of the cowl, significantly influences the spillage characteristic of the scramjet inlet

    闡明了側板后掠的側壓進氣道設計參數對構型溢流影響;對不同側板配置方式的側壓式進氣道進行了數值模擬，通過對比分析，發現由唇口板的位置所決定的溢流窗面積的大小對進氣道溢流特性的影響顯著。
  10. In this paper, simple reacting flow model in solid - propellant ducted rocket combustor based on eddy break - up model is established. the model is used to simulate the three - dimensional combustion flowfields in an experimental motor. some factors how to affect the combustion efficiency are discussed in the paper, including air intake and gas generator nozzle

    本文基於簡單反應的旋渦分裂模型，建立了固體火箭沖壓發動機補燃室內的湍流燃燒模型，並在該模型下對某實驗發動機進行了三維數值模擬，研究了補燃室設計參數包括進氣道出口設計參數和燃氣發生器噴管設計參數對燃燒效率的影響。
  11. The mixing of air and fuel can be improved, d ) adding air distributary valve at exit of air - intake can increase the amount of air bifurcated into the dome region, so the value of combustion efficiency is increased, e ) increasing gas generator nozzle number can improve combustion characteristics in the dome region and produce good condition for combustion progress, f ) when the fuel streams are ejected into the second combustor with a angle, the combustion efficiency is increased, g ) when the speed of fuel streams increased, the intension and temperature of recirculation region is improved

    兩個進氣道在補燃室周向成180度布置，有利於增強燃氣同空氣的摻混； 4在進氣道出口增加空氣分流擋板，有利於增加進入頭部的空氣流量，提高燃燒效率； 5增加燃氣噴管數量能增強燃氣同空氣在頭部的燃燒效果，為燃燒的進行創造良好的條件； 6
  12. In this thesis, hypersonic sidewall compression inlet ' s self - starting characteristics are numerical simulated and tested. with increasing mach number of inflow gradually, the hypersonic sidewall compression inlets can self - start. compared with the hypersonic sidewall compression inlet starting directly, characteristics are different. moving cowl, decreasing interior contraction ratio also can realize the hypersonic sidewall compression inlet ' s self - starting because of separation bubble on sidewall spilling out

    其次，在數值模擬結果的基礎上，設計了實驗模型和裝置並在馬赫3 . 85的風洞中進行了移動唇口板減小內收縮比實現側壓式進氣道自起動的風洞實驗，驗證了數值模擬的結果。
  13. It is no effect on a sidewall compression inlet ' s starting characteristics while a starting sidewall compression inlet is moved cowl to increase interior contraction ratio appropriately. back pressure effect on characteristics of self - starting for hypersonic sidewall compression inlet is tested in mach 3. 85 wind tunnel. the hypersonic sidewall compression inlet with interior contraction ratio 1. 24 can self - start. unstart hypersonic sidewall compression inlet caused by high back pressure can self - start by moving cowl to decrease interior contraction ratio

    最後，實驗研究了反壓對側壓式進氣道自起動特性的影響，內收縮比1 . 24的側壓式進氣道可以實現自起動並且實驗驗證了由於反壓過高而不起動的側壓式進氣道，通過移動唇口板以減小內收縮比可以實現側壓式進氣道的自起動。
  14. When the serpentine inlet is running at the exit mach number ma ( subscript e ) = 0. 45, the total pressure recovery coefficient equals 0. 90, and synthesis distortion equals 13. 85 %

    本研究的蛇形進氣道在出口馬赫數為0 . 45時，總壓恢復系數為0 . 90 ，綜合畸變指數為13 . 85 % ，總壓恢復較低，畸變較大，超出了一般航空發動機的承受范圍。
  15. The results show the exit back pressure and length / height ratio of isolator have great impact on exit flow field and starting performance of inlet. high back pressure of inlet will result in unstart

    研究表明：隔離段長高比對進氣道出口參數影響較大；隔離段出口反壓不能太高，否則會引起進氣道不起動。
  16. With computations and analysis, the comprehension on the mixing and combustion process is increased, and some significative results are listed below : a ) there are three recirculation regions and one vortex region in the combustor, and these recirculation regions affect the combustion process deeply, b ) increasing side - arm angle and moving side - air inlet position toward the fuel inlet can improve mixing and combustion characteristics, and increase the combustion efficiency, c ) when the angle between two air - inlets equals to 180

    通過計算與分析，增進了對補燃室內摻混燃燒過程的理解，為固體火箭沖壓發動機補燃室設計提供了一些有意義的結果： 1補燃室內的流動十分復雜，存在三個迴流區和一個旋渦區，迴流區對摻混燃燒過程有重要影響； 2增大空氣入射角度、向前移動進氣道出口位置有利於增強頭部迴流區強度，增強摻混效果，燃燒效率上升； 3
  17. The rib geometries have remarkable influence on the discharge coefficients of the film holes, by affecting the second flow pattern in the passage and reattachment point of the main flow ; 2

    通道內不同位置處的氣膜孔的流量系數不同，通道中後部的氣膜孔的流量系數最高，而通道進口處的較低； 3
  18. Cnpc will import 30 billion cubic meters of natural gas through a gas pipeline planned for central asia

    中國石油天然氣集團公司將通過計劃在中亞地區修建的天然氣管道進口300億立方米天然氣。
  19. The influence of intake - valve port offset on three - dimensional flow field in four - valve diesel engine

    進氣道偏置對四氣門柴油機進氣門口三維流場的影響
  20. Experimental results of the air pumping of a serpentine inlet under ground running show that the total pressure recovery at the exit is low and the distortion at the exit is large

    摘要對一種蛇形進氣道開展了地面工作狀態下的抽吸試驗研究，結果表明，在該狀態下進氣道出口截面的總壓恢復系數較低、流場畸變較大。
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