fuel flow pressure 中文意思是什麼
fuel flow pressure
解釋
燃料供給壓力-
The portion of the carburetor air horn that reduces pressure to cause fuel to flow is called the venturi.
減少引起燃油流動壓力的化油器空氣喇叭口部分稱為喉管。 -
The effects of such elements as primary flow total pressure, flow rate, degree of fuel rich, nozzle structure, flying speed and secondary combustion on ejecting mode performance were researched. it was found that thrust augmentation can be achieved on the condition that the flying mach number is above 0. 7. to deeply analyze thrust augmentation mechanism in low speed range, the research was further continued by changing secondary combustion organization and aft - body configuration
研究了一次流總壓、流量、富燃程度、噴管結構、二次流來流速度、二次燃燒組織對引射模態性能的影響，發現實驗樣機構型在0 . 7ma以上的飛行條件下可以獲得推力增強，而在0 . 7ma以下無推力增強。 -
In addition, considering the essential characteristics of the fusion - fission hybrid reactor, the preliminary analysis and research of the mhd pressure drop of liquid metal that flow through the fuel packed pebble bed - based blanket are given
另外，基於聚變中子源驅動的次臨界清潔核能系統，針對聚變?裂變嬗變混合堆的本質特點，對液態金屬球床包層進行初步地探討和研究，進行了球床液態金屬溢流的磁流體動力學流動的建模分析和計算。 -
The accurate models of steam pressure controlled system were established in accord with the theory of marine boiler. the response was compared with that obtained through simulation realized by the use of matlab and actual process on different steam flow, fuel flow and control method
運用matlab模擬工具，對汽壓調節對象模擬模型在不同的蒸汽負荷、不同燃油量和不同控制方式下的動、靜態情況進行模擬比較，提出不同控制要求下的控制演算法。 -
Four conclusions were obtained : 1 ) the ideal maximum performance of rbcc engine is basically determined by the match of rbcc " s basic operating parameters such as the ratios of primary / secondary mass flow rate, total pressure, total temperature and the ratio of overall oxidant / fuel mass flow rate, etc
主要獲得如下結論： 1 ）基本工作參數的匹配，如引射比、總壓比、總溫比，決定了引射發動機最大可能獲得的性能。 -
There are great differences between ground test of a flight vehicle ' s aerodynamics and that of a dual - mode scramjet when ground test facilities are used to do experiments on a dual - mode scramjet engine, the components of incoming flow and its parameters, including total pressure, total temperature ( or total enthalpy ) and velocity must be simulated. at the same time, since the fuel ' s resident time within a combustor is very short, on the order of one millisecond, it is difficult to measure the flow - fields
進行雙模態沖壓發動機地面試驗研究時，必須要求試驗設備能模擬實際飛行條件下來流氣體的組分、總壓、總溫（或總焓）以及來流氣體的流動速度；同時由於燃料在燃燒室內駐留的時間很短，一般為毫秒量級，從而使流場物理量的測定顯得非常困難。 -
The main results are : supersonic region and subsonic region can co - exist in flow path simultaneously, subsonic flow is insignificance for engine performance ; total pressure of primary rocket should be decreased when mach number is increased. in the experimental aspect, some components of ejectorjet experimental system were improved, ejectorjet experiments using alcohol as secondary fuel were conducted
由數值計算獲得的結論為：引射火箭內的一般流態為超音速區與亞音速區共存，亞音速區不具備做功能力；飛行馬赫數增大，引射火箭內更易於產生壅塞；為了獲得最佳的性能，隨著飛行馬赫數的提高，應當降低一次火箭的工作壓強。 -
It is shown that when the exit area of secondary nozzle and the fuel / oxidizer ratio is fixed, the increase of mass flow rate of secondary flow lead to the decrease of velocity of mixed flow, and increase of total mass flow rate. the synthetical result of these two phenomenon cause the increase of thrust of rocket ejector, but the increasing magnitude is relatively small, indicating that these is no necessary to claim large bypass ratio in rocket ejector design. in the comparison between two configurations, the typical one has better performance, indicating the importance of pressure ratio
結果表明：在固定二次噴管出口面積和氧燃比的條件下，二次流（引射空氣流）流量的增加引起混合氣體出口速度的下降和總流量的增加，二者綜合作用使發動機推力增加，但增幅不大，表明在設計發動機結構和工作參數時，不必過分追求大的引射系數；兩種結構的性能對比分析表明了增壓比對引射火箭性能的提高具有重要意義；對引射火箭的熱力循環分析同樣表明，增壓比對于提高發動機性能非常關鍵。
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