進氣 的英文怎麼說
中文拼音 [jìnqì]
進氣
英文
air admission; admission; inlet; onflow; charging; access of air; admittance; air-in; air intake; inlet gas進氣點 admission; 進氣閥 [機械工程] intake valve; admission valve; air intake valve; inlet valve; 進氣管 admitting pipe; air inlet pipe; air intake pipe; drawing lift; suction piece; wind bore; penstock; air line; snorkel; schnorkel; inlet connection; 進氣活門 air inlet valve; air intake valve; 進氣孔 air intake; 進氣口 air inlet; suction port; 進氣量 air inflow; air intake flow; inlet airflow-
Mat manifold absolute temperature
進氣歧管絕對溫度Tahir r b, molder s and timofeev e v. unsteady starting of high number air inlets - a cfd study [ r ]. aiaa 2003 - 5191
梁德旺，袁化成，張曉嘉.影響高超聲速進氣道起動能力的因素[ c ] / / 2005年沖壓發動機技術交流會論文集， 2005Review on inlet air cooling technology for gas - turbine
燃氣輪機進氣冷卻技術淺析Selection of inlet air cooling technology for gas - turbine
燃氣輪機進氣冷卻工藝的選擇Brief introduction for gas turbine inlet air cooling system
淺述燃氣輪機的進氣冷卻技術Salinity exists in oceanic atmosphere at aerosol form. usually, seacrafts need desalted air, for example, air for combustion and cooling, airiness of communication cabin and electron cabin, etc. now, lots of large naval ships are equipped with gas turbines both home and abroad
海洋大氣中含有鹽分且以氣溶膠形式存在，海洋艦船的進氣往往有除鹽要求，例如艦船發動機燃燒用和冷卻用的進氣、通訊電子艙的進氣等。Bmap barometric and mainfold absolute pressure
大氣進氣歧管絕對壓力Bi met bimetallic air temperature control sensor
雙金屬進氣溫控傳感器Pa 6 for blow moulding
吹塑級進氣管和排氣管A canister purge valve is opened periodically to vent the vapor back into induction system.
收集器的清除閥周期性地開啟，泄放蒸氣使之返回進氣系統。Carburetter air funnel
化油器空氣進氣喉管Air inlet clack valve
進氣瓣閥Numerical simulation of flows in a dual - inlet dump combustor
雙側進氣突擴燃燒室流場數值模擬Optimized carburetor catalyzer transfer machine drive - style, curved girder optimized carburetor twice air device catalyzer 50qt, footplate bike
優化化油器二次空氣進氣裝置sai催化劑On exploring design of hypersonic forebody inlet and isolator of integrated scramjet
進氣道和隔離段氣動設計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。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。The design point of the designed forebody / inlet is flight mach number m = 6 and flight attitude h = 25km. the three - ramp, mixed external and internal compression hypersonic / inlet is chosen as representative geometry to be designed. nine types of hypersonic / inlet model with difference forebody length and total turning angle are obtained that the incidence angle of the first ramp and height of isolator are given
根據飛行任務要求，以飛行馬赫數6 ，飛行高度25km為設計點，給定前體預壓縮角、隔離段高度，對具有不同前體長度和不同總壓縮轉角的帶隔離段的前體進氣道進行了設計。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。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。分享友人