燃燒力強度 的英文怎麼說

中文拼音 [ránshāolìqiángdù]
燃燒力強度 英文
intensity of burning power
  • 燃 : 動詞1. （燃燒） burn 2. （引火點著） ignite; light
  • 燒 : Ⅰ動詞1 （使東西著火） burn 2 （加熱或接觸某些化學藥品、放射性物質等使物體起變化） cook; bake; hea...
  • 力 : Ⅰ名1 （力量; 能力） power; strength; ability; capacity 2 [物理學] （改變物體運動狀態的作用） forc...
  • 強 : 強形容詞（強硬不屈;固執） stubborn; unyielding
  • 度 : 度動詞[書面語] （推測; 估計） surmise; estimate
  • 燃燒 : （物質劇烈氧化而發光、發熱; 燒） burn; kindle; flame; set on fire; [化學] combustion; inflammation; ignition
  1. Energy consume, electric strength, insulation resistance, ground conductivity, leakage current, microwave leakage, power input, normal temperature, humidity treatment, glow wire, horizontal flame, vertical flame, tracking, ball pressure, rainproof, water splash, dustproof, salt fog, endurance, motor load test, cord flexing, cord pulling, pull & torque test, lamp replacement, construction check etc

    能耗、電氣強度、絕緣電阻、接地連續性、泄漏電流、微波泄漏、功率、溫升、濕熱試驗、灼熱絲、水平燃燒、垂直燃燒、漏電起痕、球壓試驗、防雨淋、防濺水、粉塵、鹽霧、耐久性（壽命）試驗、電機負載試驗、電源線彎折、電源線提拉、拉扭力測試、燈頭互換性、安全結構檢查等。
  2. In this paper, firstly the macro parameter of the series connection app was comprehensively analyzed, among which the trajectory location of the bullet emission and the terminal velocity of the bullet were mainly analyzed, and the feasibility of the series connection app to cope with explosive reactive armor was demonstrated. and then the macro design about the head of the series connection app was made, among which a particular analyse about the bullet " s launching process was made, from which we concluded the relation between the thickness of the airproof loop and the velocity of the bullet detached from the carrier and the relation between the length of the bullet and the velocity of the bullet detached from the carrier and the relation between the length of the bullet and the burning rate of the powder and the relation between the length of the bullet and the maximum pressure of the emission hole and the relation between the length of the bullet and the emitting time of the bullet, and the reasonable str ucture of the head of the carrier and bullet were designed, then the intensity of the head of the carrier was checked out using of the software of ansys

    本文首先對子母式穿甲彈總體參量作了全面的計算分析，其中主要分析了子彈射出的彈道位置和必要的子彈著靶速度，論證了子母式穿甲彈對付爆炸式反應裝甲的可行性，然後對子母式穿甲彈彈頭部進行了總體設計，其中主要對子彈的發射過程進行了詳細的分析，得出了母彈彈頭部發射孔內閉鎖環厚度與子彈飛離母彈速度的關系、子彈長度與子彈飛離母彈速度的關系、子彈長度與火藥燃燒率的關系、子彈長度與母彈彈頭部發射孔內最大壓力的關系以及子彈的長度與子彈發射所需時間的關系，設計出了合理的母彈彈頭部結構和子彈的結構，並利用ansys有限元分析軟體對母彈彈頭部的強度進行了校核。
  3. 3. on boiler retrofit, the calculation of fuel burning, the heat calculation of boiler inside structure and convection section, and the design of structure parameter of feed water heat exchanger are made. the flue gas channels " resistance calculation and the boiler strength verifying are also carried out. replacement of water cooling wall improves heat exchanging and decreases loss of heat radiant

    對鍋爐本體進行了燃料燃燒計算、爐膛結構熱力計算、對流受熱面結構熱力計算、鍋爐給水加熱器結構參數設計、煙道阻力計算及鍋爐元件強度校核等；改進了水冷壁布置使換熱效果更好，減少輻射換熱損失；改進對流段結構，更充分的利用爐膛出口煙氣余熱，提高熱效率；並且進行了煙氣阻力計算、熱效率計算和能量平衡測試，對改進后的稠油燃料和改進前進行了對比，燃燒狀況和熱效率有明顯改善。
  4. Results show that all the geometric parameters have remarkable effects on combustion performance ; the swirl of intake air generated by skew intake holes enhances fuel - air mixing, minimizes dead zone and stabilizes the flame with reverse flow, but the excessive reverse flow can cause overheat in combustion chamber and exhaust ; the consistency of flow resistance in intake and exhaust system is conducive to the stability of heater performance

    研究表明，燃燒室進氣孔的孔徑、孔數、孔的分佈及方向等均對燃燒性能影響很大；斜孔所產生的旋轉進氣，雖具有強化燃氣混合、消除死區和迴流穩焰的作用，但迴流過度會使燃燒室及排溫過高；保證進排氣系統流動阻力（壓力）的一致性，有助於保證加熱器性能穩定。
  5. This experiment studies the relation of ionic current signals and a / f ratio on different premixed pressure

    通過控制預混壓力和空燃比兩個參數變化，消除了由於發動機循環變動對燃燒狀態和離子電流強度的不穩定影響。
  6. Microstructure of the composite layer was analyzed with help of optical microscope, scanning electronic microscope ( sem ), electronic probe microanalysis ( epma ) and x - ray diffraction ( xrd ). the compacting of the billet and the forming mechanism of the carbide reinforcement were studied based on thermodynamics and kinetics of reaction, sintering theory and the result of dta. at the same time, the wear - resistance of the composite layer was studied under condition of dry sliding friction

    利用光學顯微鏡、掃描電子顯微鏡、電子探針以及x -射線衍射儀，分析了表面復合層的基體組織結構；運用反應熱力學、動力學、粉末燒結理論和燃燒合成理論，結合差熱分析結果，探討了表面復合層壓坯的燒結緻密化原理和碳化物增強相的形成機理；利用坯塊在真空燒結爐不同溫度下的燒結出來的顯微組織分析，模擬出坯塊的燒結過程中的化學反應過程。
  7. 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。
  8. 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。
  9. The experimental results indicates that the secondary mass flow increases with increasing of primary mass flow rate, but the bypass decrease because the primary mass flow rate increase more rapidly than secondary mass flow. the expansion configuration shows low thrust property due to low pressure in flow path. the secondary nozzle changes the pressure distribution in ejector combustor, and decreases bypass ratio, but obtain more completely mixing

    結果表明：二次流流量隨著一次流流量的增加而增加，由於二次流流量的增加速度低於一次流，引射系數減小；在純擴張式結構實驗中，引射燃燒室壓強很低，難以實驗推力增強；二次噴管改變了引射燃燒室的壓強分佈，降低了引射系數，改善了混合狀況能；對于本文的實驗結構，存在一個最優的二次噴管出口面積，使引射火箭推力最大，同數值模擬結果相吻合。
  10. Besides, in this paper, the velocity distributes and recirculation areas of two phases are shown, and the differences between simulations and experiments are diminutive. turbulence kinetic energy ( ?, turbulence dissipation rate ( e ), reynolds stress and turbulence intensity are also simulated to reflect turbulence flow

    另外，本文計算了旋流燃燒器內氣固兩相的速度和迴流區的分佈，並和已有的實驗數據進行了比較，同時還計算了湍動能、湍能耗散、雷諾應力和湍流強度等反映湍流的物理量。
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