inlet boundary 中文意思是什麼
inlet boundary
解釋
入口邊界-
Second, the starting and stopping behaviors under disturbed condition are analyzed and calculated by using the dynamic concentrative parameter model, which gives some advice to better prescribe refrigeration system and set theoretic foundation for carrying out automatic control of refrigeration system. third, the normal running process is analyzed and calculated by means of rational matching theory, which gives some advice on how to better understand the parameter change under steady state and the affection of inlet - parameter on evaporator. fourth, the simulation software with dynamic characteristic is designed, which can be applied to calculate thernio - parameter of cryogen, air humidity and frost thickness under different initial and boundary conditions, and to carry out dynamic simulation under conditions of dryness, wetness and frostiness, at the same time, to achieve detection and simulation at any stage from starting to stopping
本文的主要內容如下： 1 ）對翅片管蒸發器結構特點進行分析，選取適當的微元控制體，就干、濕和霜工況下對每個微元分別進行傳熱傳質分析，基於經驗關系式確定霜的有關參數，對于霜工況下的霜生長建立模型，經適當假設，運用質量守恆、能量守恆和動量守恆方程建立適合動態模擬的蒸發器數學模型，為系統模擬奠定基礎； 2 ）對蒸發在大擾動下的開、停機過程，運用動態集中參數模型進行分析和計算，為更好地描述製冷系統運行的全過程奠定基礎，同時也為製冷系統實現自動控制提供一定的理論基礎； 3 ）對蒸發器正常運行過程，運用動態分佈參數和參數間定量耦合的觀點來分析和計算，為更好地了解穩態工況下各點參數的變化情況及各入口參數對蒸發器動態特性的影響即蒸發器性能對各參數變化的敏感性； 4 ）編寫翅片管蒸發器動態特性模擬計算程序，可以計算不同邊界條件和初始條件下的製冷劑熱力參數、空氣溫濕度和霜厚度分佈場，實現對翅片管蒸發器在干、濕和霜工況下的動態模擬。 -
This demonstrates that for propulsion - airframe integration, this genus of inlet would be advantageous in keeping the stability of boundary layer coming from the forebody
一體化設計時，該進氣道對保持前機體來流附面層的穩定性十分有利。 -
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。 -
Experiment of boundary layer suction in serpentine inlet under ground running
蛇形進氣道地面工作狀態附面層抽吸試驗研究 -
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。 -
Certain discrepancy remain between the simulation results and the experiment results, not only caused by the turbulent model, but also by the simplification of the inlet boundary condition and the mesh generation. modeling gas - particles interaction flows is complex. in this thesis, gas - phase transport equations coupled with the gas - particle interaction are derived based on the dsm turbulent models to handle the interaction of momentum and kinetic energy of turbulence between the gas and particles
分離器內的固體顆粒運動採用涉及湍流擴散影響的隨機軌道模型和確定軌道模型，同時在湍流模型中加入了顆粒影響的源項，在流場計算的基礎上，模擬了不同直徑的顆粒在分離器內的運動規律及顆粒分離效率，並同理論和實驗得到的數據進行了比較。 -
Then author discusses the writing and debugging of the program. the ventilation of a typical chamber with a stable fixed pollutant emission is studied by founding different boundary conditions ( here, they are the both up inlet and outlet on opposite side, the up - inlet and down - outlet on opposite side and the up - inlet and down - outlet on the same side. ). and accordingly dividing different grids. using the program, the velocity values and the pollution concentration values of the chamber are worked out
對所研究的具有單個固定污染源的典型房間的室內通風，通過對異側上送上排、上送下排以及同側上送下排等幾種方式下，建立相應的邊界條件並劃分網格，運用編制的程序對它們進行數值模擬，所得的計算結果再用excel軟體分別進行顯示與處理，得到相應條件下的流場、濃度場，而後再算出相應的通風效率。 -
Turbulence over flat wall is presented with the cfd software cfd ace ( u ) when given by various inlet boundary conditions, subgrid model and turbulence intensity under the two - dimensional circumstance. on comparing these outcomes with the experimental data, we can analyze the impacts that all these factors have on the development of flow boundary layer
採用計算流體力學軟體cfdace （ u ） ，在二維情況下應用不同的進口邊界條件、亞格子模型和來流湍流度對平壁流動進行大渦模擬，並將模擬結果與已有的實驗結果進行對比，分析比較了這些因素對流動邊界層發展的影響。 -
The numerical simulation of the inlet flow fields in the gas turbine. obtained numerical simulation results of flow fields include the uniformity, with the geometrical boundary completely according with the actual one and nothing being simplified
在幾何邊界形狀上嚴格反映物理真實而不作任何簡化，獲得了整個進氣系統地流場分佈狀況和壓氣機進口截面的不均勻度。 -
Horizontal circulation at the inlet of the upper approaching channel of three gorges project can affect the safety of navigation. boundary layers will separate along a curved dike causing horizontal circulation regions which affect the overall flow field and increase sedimentation
類似的由於流動邊界出現凸出障礙物引起邊界層分離，導致迴流發展、流態惡化，造成泥沙淤積等一系列問題的情況，在水利、航道及電站等工程中普遍存在。 -
The physical and mathematical models are founded. numerical simulation of marangoni convection in the liquid bridge and gas channel was performed by employing the primitive variable method and using galerkin finite element method, which is applied for discretization of non - dimensional governing equations and boundary conditions. the relationship between the suppressing status of mc in the liquid bridge and the inlet gas velocity or the channel width is obtained, and the suppressing status of some kinds of marangoni numbers ( ma ) or size ratios of liquid bridge a is analyzed
採用原始變量法，用galerkin有限單元法對無量綱控制方程及邊界條件進行離散后，數值模擬了微重力條件下半浮區硅熔體及氣體流道內的marangoni對流，得出了無量綱氣流沖刷速度及流道寬度變化和熔體內熱毛細對流抑製程度的關系，進而分析了不同的無量綱參數ma數和不同熔體幾何尺寸比a下熱毛細對流抑制情況。 -
The simulation was began based on defining the boundary which was coupled with heat and mass transfer. numerical simulation was performed with different inlet velocity, temperature, water vapor concentration and channel width
對于數值模擬的結果，採用后處理工具tecplot等進行處理，得到了一、二次空氣通道內的壓力、速度、溫度以及水蒸汽濃度的分布圖。 -
The hub leakage flows were modeled and calculated in two different ways : the flow fields inside hub axial gap were calculated together with blade passage flow in an integrated manner, and the leakage flows due to the hub axial gap were modeled as inlet boundary conditions
計算時分別採用了兩種模化途徑，即耦合求解轉子上游葉根間隙內空腔與轉子通道內的流場，以及求解將葉根同間隙模化為進口邊界的轉子流場。 -
Results from this investigation show that the loss generation within the coolant holes is substantial and that ejection into regions of low static pressure increases the loss per unit coolant mass flow. the results also reveal strong interactions between endwall coolant ejection and secondary flow in the blade passage. the secondary flow has a strong influence on coolant trajectories and coolant ejection delays the three - dimensional separation of the inlet boundary layer on the endwall, chang the secondary flow and reduces its associated losses
本文的研究成果顯示，冷卻孔內產生的損失是主要的，並且低靜壓區域的冷空氣噴射會增加單位冷空氣質量流的消耗；噴射的冷空氣與葉柵端壁流場之間有強烈的相互作用；二次流對冷卻空氣的流動軌跡有較強的影響；冷空氣噴射能延緩端壁入口邊界層的三維分離、改變二次流從而減少其相關損耗。 -
Then the pro ? models have been input into pro ? m, an automatic mesh generating software, to create the mesh system for numerical simulation. after defining some proper boundary condition, the flow analysis have been performed through the use of star ? d, a powerful cfd software. with some careful analysis of the simulation results and comparison of the two models, some guiding principles for the design optimization of the compressor inlet turning tubes have been concluded
論文主要工作包括：通過對壓氣機進氣彎管幾何形狀的深入分析，利用三維建模軟體pro / e生成其三維幾何模型；利用網格自動生成工具pro - am ，根據pro / e生成的三維幾何模型生成了數值模擬所用的計算網格；對壓氣機進氣彎管內部流動進行了詳細的氣動計算，對原進氣彎管與新型進氣彎管的計算結果做了對比分析，對其結構的優化設計提出了指導原則。
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