渦動室 的英文怎麼說

中文拼音 [guōdòngshì]
渦動室 英文
vortex chamber
  • 渦 : 渦名詞1. （漩渦） eddy; whirlpool; vortex 2. （酒窩） dimple
  1. Hsc high swirl combustion engine

    強渦流燃燒室發動機
  2. Although a dual - mode scramjet ' s configuration is simple and mainly consists of inlet, combustor and wake nozzle, its working process is complicated, especially in the combustor, involving a lot of subjects, including hypersonic aerodynamics, combustion chemistry, etc. the inner flow of a combustor is three - dimensional and complicated, including the interaction of shock wave, deflagration, vortex and boundary layer, and so on

    它涉及到高超聲速空氣動力學、燃燒化學、擴散傳質等多門學科；其內部的實際流動是復雜的三維流動過程，充滿著激波、膨脹波、燃燒波、各種渦系、附面層及其相互之間的干擾，因此，燃燒室問題是整個發動機研究的關鍵所在。
  3. With piv technology, the flow field was measured to judge the performance of pump sump. by analyzing the pictures of velocity, streamline, turbulent kinetic energy and vorticity, we found that the turbulence was bigger while the ratio of the runoff increased. and the vortices always appeared in the field where the runoff was small

    通過piv試驗，測量了封閉式水泵吸水室內部的流場，以研究該水泵吸水室的性能； （ 2 ）通過分析流速圖、流線圖、湍動能圖和渦量圖，發現了流量比越大，湍動越大，漩渦總是出現在流量較小的一側。
  4. 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。
  5. Abstract : this paper briefly presents th e application of advanced brazing techniques for a larye number of assemblies of space vehicles, such as thrust chamber and turbine rotor of launch rock et engine, titanium tube of satellite, attitude control engine injector and wave guide component of satell ite, reflector, tube and honeycomb panel of manned spacecraft, main engine nozzl e and preburner of space shuttle as well as the pipeline systems of space statio n

    文摘:簡略地介紹了先進釬焊技術在航天器部件，例如運載火箭發動機的推力室和渦輪轉子、人造衛星的鈦導管、姿控發動機噴注器和波導器件、載人飛船的反射器、導管和蜂窩壁板、航天飛機的主發動機噴管和預燃室以及空間站的管路系統等的廣泛應用情況。
  6. 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。
  7. The precondition of establishing mathematics model of torpedo turbine system in design condition is to fulfill the external conditions ( such as torpedo sailing speed and depth etc. ) and inner conditions ( such as turbine power and efficiency etc. ). after establishing mathematics model of torpedo turbine system in design condition, we compiled simulation program to compute all kinds of inner parameters of turbine engine include engine type, principal layout of turbine, inner structure of turbine and state parameters of gases

    首先分析設計工況時渦輪機動力系統，在滿足魚雷動力系統的各項外部條件（如魚雷航深、航速等）和內部條件（如渦輪機功率、效率，燃燒室壓力、溫度，轉子機械強度等）的前提下，建立起設計工況渦輪發動機的數學模型，編程計算並確定渦輪機內部機械結構和燃氣熱力學狀態各參數。
  8. 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。
  9. And the finite element method ( fem ) was used to simulate the stress and deformation of the outer casing and the bearing chock. on the basis of the experiments and fem analysis, the strength and fatigue lifetime, the interaction of creep and fatigue lifetime, the creep lifetime of outer casing and bearing chock have been analyzed, at the end of trail, sem analyses of failure section has been conducted

    同時對航空發動機燃氣渦輪外機匣和軸承座進行了有限元模擬計算，得到外機匣和軸承座的焊接處的強度和變形情況的模擬結果。根據試驗數據和有限元的計算結果，對發動機燃燒室外機匣和軸承座兩種結構（包含焊縫）進行靜強度分析、疲勞壽命分析、蠕變壽命分析、蠕變疲勞交互作用壽命分析以及斷口的金相分析。
  10. Based on prandtl ' s momentum transportation, this paper calculates in detail the physical quantities such as eddy viscosities, and ratio of eddy viscosity to motion viscosity, total stresses with respect to relative position in three regions of viscous sub - layer, buffer layer, and main turbulent stream for non - newtonian fluid flowing turbulently in ducts, which according to karman ' s three layer models and measurement of fluid parameters in evaluation apparatus, discusses the influence of polymer drag reduction on flowing properties of non - newton fluid, analyzes quantitatively principle of turbulent reduction phenomenon and condition of increasing reduction rate

    摘要以普蘭德動量傳遞理論為基礎，按照卡門的三層模型，通過室內模擬環道用0號柴油及加入減阻劑在圓管內的流動參數的測定，計算了非牛頓型流體管內湍流邊界層的層流內層、過渡層、湍流中心的渦流粘度，渦流粘度與運動粘度比、總應力隨相對位置的變化等定量參數，探討了高分子減阻劑對非牛頓流體流動特性的影響，對湍流減阻現象的機理與增大減阻率的條件進行了定量分析。
  11. Based on the combustion model, the intermediate combustion products, the rate of the heat release in the swirl chamber, the engine ' s transient pressure and temperature are traced in details during the calculation

    在此模型基礎上，對發動機缸內燃燒的中間產物、渦流室的放熱率、缸內瞬時壓力和溫度進行了分析。
  12. Could be scooped into a methane digester, a device that uses bugs and microorganisms to gobble up the material and emit methane, which would be trapped and burned to power a turbine to make electricity or to heat

    狗糞將被倒入一個沼氣消化池的裝置，然後被蟲子和微生物分解並釋放出沼氣。而這些沼氣被收集起來，燃燒之後可以帶動渦輪發電或者給室內供暖。
  13. Could be scooped into a methane digester, a device that uses bugs and microorganisms to gobble up the material and emit methane, which would be trapped and burned to power a turbine to make electricity or to heat homes

    狗糞將被倒入一個沼氣消化池的裝置，然後被蟲子和微生物分解並釋放出沼氣。而這些沼氣被收集起來，燃燒之後可以帶動渦輪發電或者給室內供暖。
  14. 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。
  15. In this paper, a calculation method of combustion heat release rate for the swirl chamber coal - bed gas engine is concerned. it can be a useful tool on analyzing the combustion processes for this type engine

    另外，本文開發了一個渦流室式火花點火煤層氣發動機放熱率計算軟體，為分析這類發動機缸內燃燒過程提供一個有效的工具。
  16. In this paper, maccormack explicit time - split scheme, baldwin - lomax algebraic turbulent model and two - steps hydrogen - air nonequilibrium chemical kinetics model are employed to simulate the 2 - d flow fields in a fixed geometry scramjet combustor in different injecting way of fuel in different flight conditions. the results show, in the same entrance condition, the operating mode of scramjet combustor is influenced by the control of fuel

    本文採用maccormack顯式時間分裂法、 b - l代數渦粘性湍流模型及氫-空氣兩步非平衡化學動力學反應模型，模擬了在不同的飛行馬赫數條件下，固定幾何的雙模態燃燒室在不同供油規律下的二維燃燒流場。
  17. 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
  18. Tests have been carried on a swirl - chamber diesel engine fueled with diesel oil - methanol - water composite fuels. the effects of using different diesel oil - methanol - water composite fuels are shown. angles of injection and proportion of water in methanol which have influence on the effect of using diesel oil - methanol - water composite fuels are investigated

    在渦流室式柴油機上進行了燃用柴油-甲醇-水三元乳化液的試驗研究，得出了各種柴油-甲醇-水三元乳化燃料的使用效果，並探討了供油角、甲醇中的含水量對發動機性能的影響。
  19. A simulation of the generation of the nox has been done on the base of the novel model of the combustion theory of the swirl chamber, which has been established in this paper

    在理論上，建立了新的渦流室式lpg柴油雙燃料發動機燃燒的準維燃燒模型，在此模型下，對no _ x的生成機理做了計算機模擬模擬，並與試驗結果進行了比較和分析。
  20. With the pressure measurement system for the swirl chamber diesel engine, by using the methods of equivalent power and the seven point three degree average for the indicator diagram, we can correct the tdc, smooth the pressure curve and make more accurate pressure data that is a well basis for the calculation of combustion heat release rate

    摘要本文在自行開發的渦流室柴油機壓力數據測錄系統的基礎上，利用等效功法和七點三次加權移動平均法，分別對示功圖進行了上止點校正和壓力曲線光順，使壓力數據更精確，為燃燒放熱率的計算打下了良好的基礎。
分享友人
分享到 Line

分享到臉書