航空力動機 的英文怎麼說
中文拼音 [hángkōnglìdòngjī]
航空力動機
英文
aeromotor-
Jet engines with which most modern high-speed aircrafts are equipped develop thrust on the same principle as the propellers of conventional aero-engines.
大多數現代高速飛機裝備的噴氣發動機產生推力的原理，與普通航空發動機的螺旋槳相同。A component level aerothermodymamic model of a turbofan aeroengine is created in this thesis using oo technology
本文基於面向對象技術建立了某型雙軸渦扇航空發動機的部件級氣動熱力模型。Accounting for creep and stress relaxation, a long - term life and low cycle fatigue life prediction method for gas turbine engine hot section is established
摘要建立了考慮蠕變和應力鬆弛的航空發動機渦輪葉片等高溫構件的持久壽命和低循環疲勞壽命預測方法。Compress disk is the very important rotational component in the areoengine. when the compress disk is working, the grads of temperature and stress between the rim and the center of the disk are great. in order to raise the thrust - weight ratio of the disk and reduce oil consumption. the best prospective way is the dual alloys disk used
壓氣機盤是航空發動機上一個很重要的轉動部件，壓氣機盤工作時，輪緣和輪轂溫度梯度和應力梯度較大，為了提高飛機發動機推重比、減低耗油量，要求壓氣機盤的工作溫度、使用性能更高，雙合金盤製造是最有發展前景的技術。The main contents of this paper are following. ( 1 ) the mechanical models of ball bearings are set up by both the quasi - dynamic method and the finite element method in this paper, and then the load distribution of ball bearings is studied. the rules of the contact angle, the deformation, the stiffness and the limit rotational speed in different structure parameters and load parameters are analyzed
本文圍繞航空發動機高速滾動軸承的力學特性，開展了以下工作: （ 1 ）分別採用擬動力學法和有限元法，建立了滾動軸承力學分析模型，研究了滾動軸承的載荷分佈特性，分析了不同結構參數和載荷參數對其接觸角、變形、接觸剛度和極限轉速的影響規律。3. bring forward a new idea : the ideology of synergetics used in atomic simulation and multi - scale simulation of materials design. on the basis of this, next tasks were put forward : ( 1 ) analyzing the changes of stress - strain curves of the interphase before and after pre - treatment ; ( 2 ) the efficient of the coupling effect of o2, na2s04 and h2o stream on the oxidation and erosion resistance of interphase ; ( 3 ) the methods of improving environment performance of interphase above 1273k
提出將協同學的思想用於原子級模擬及跨尺度模擬的思路，並在此基礎上，提出下一步的工作設想： （ 1 ）分析熱處理前後界面相區域應力-應變曲線的變化； （ 2 ）航空發動機模擬環境中，氧、硫酸鈉蒸汽及水蒸汽耦合效應對界面相抗氧化性、抗腐蝕性的影響； （ 3 ） 1273k以上界面相環境性能提高的方法。Thus the safe and reliable operation of the aeroengine, which supplies the major motive power to the modern aircraft, plays undoubtedly the first important role in this field ; and accordingly the status inspection of the aero - engine operation and the fault diagnosis technology have become the research focuses during the recent years
安全是現代航空工業尤其是民航運輸工業的首要要求，而作為現代飛行器的動力核心，航空發動機的安全、可靠運行則是重中之重，因此，航空發動機運行狀態監測與故障診斷技術也就成為當今的研究熱點。The pressure parameters testing of airplane engine is based on zero dead time parallel acquisition technology to test the pressure signals which were tranfered from pressure sensor
航空發動機脈動壓力的測試基於多通道無間隔并行採集技術，對壓力傳感器傳送的脈動壓力信號進行採集測試。Transient dynamical analysis of aero - engine combustor outer casing
航空發動機燃燒室外機匣瞬態動力分析The measurement system is based on pci bus and designed to integral measure the engine ’ s parameters such as pressure, engine rotate speed, air flux, etc. the system is very important in evaluatiang 、 ameliorating and repairing airplane engine because it provides relevant exam data for the airplane engine design
該測試系統基於pci總線，對發動機的脈動壓力、轉速擺動、燃油流量等參數進行綜合測試，為航空發動機的研製提供相應的試驗依據，對發動機的性能評估、技術改造、故障維修等具有十分重要的意義。Directionally solidified refractory metal matrix eutectic in - suit composites possess excellent mechanical and physical properties such as low density, high enduring temperatures, good room - temperature fracture - toughness and high elevated - temperature strength, therefore are expected to be used as a new type of ultra - high temperature structural materials
定向凝固難熔金屬基共晶自生復合材料由於具有密度低、承溫能力高、室溫斷裂韌性好、高溫強度高和高溫持久壽命長等性能優勢，有望成為新一代航空發動機葉片用超高溫結構材料。To study the aircraft - engine stability assessing technology about total - press distortion, four different structure insert - boards and testing schemes are designed, based on the technology of russian insert - board distortion and assessing compressor stability of english and usa. the low speed compressor ( lsc ) at college of energy and power in nuaa is used to carry out the all insert - board distortion experiments studies
為了能夠更清楚地認識俄羅斯關于總壓畸變下的航空發動機穩定性評定的技術，本文在了解俄羅斯插板畸變試驗技術和英美等國家的穩定性評定技術的基礎上，設計了4塊不同結構形式的插板畸變擾流器裝置及試驗測量方案，利用南京航空航天大學能源與動力學院的低速大尺寸軸流壓氣機（ lsc ）試驗器，完成了各插板的畸變試驗。An aeroengine power - turbine 1 ( superscript st ) stage rotor shrouded blade is taken for an example in the article, tightness of shroud and contact force 、 blade body stress under working state and assembly state are calculated by finite element contact analysis method, influence of working load ( temperature and centrifugal force ) is mainly analyzed
摘要以航空發動機動力渦輪一級帶鋸齒形葉冠的轉子葉片為例，用有限元接觸分析方法對裝配和工作狀態下的葉冠緊度和葉冠接觸力、葉身應力進行了計算和分析，著重考察了工作載荷（溫度和離心力）對葉冠接觸力的影響。The efficient boundary element method is improved in this paper to deal with open multi - layer structures, and used to analyze thermal barrier coated components of aero - engine, which further enrich the former research
本文將薄體多層結構邊界元法分析推廣用於開環型多層結構分析，進一步豐富了以前的研究成果，並利用它分析航空發動機帶熱障塗層葉片熱應力。Carbon fiber reinforced silicon carbide composite ( c / sic ) is one of the most promising thermal - structure materials up to 1650 for aero engines. it is very significant to deeply understand the oxidation mechanisms and establish the oxidation kinetic models for the design and application of c / sic composites
C sic復合材料是一種有希望滿足航空發動機熱端部件1650工作溫度需要的結構材料，深入了解其氧化機理並建立氧化動力學模型對c sic復合材料的設計和應用具有重要的指導意義。Powder metallurgy turbine disks are worldwide adopted in most advanced aeroengine nowadays. the research of engineering application of them is actively being carried out in our country, and the key problem urgently needed to solve is their low cycle fatigue life prediction. the low cycle fatigue failure of powder metallurgy turbine disks is mainly caused by inclusions, so it ' s important to study the effect of inclusion on the stress intensity factors ( sif ) initiation and development of crack in powder metallurgy turbine disks
當前世界上大多數先進航空發動機均採用了粉末冶金渦輪盤，我國目前正在積極開展粉末冶金渦輪盤的工程應用研究，其低周疲勞壽命預測成了亟待解決的關鍵問題，夾雜物是引起其低周疲勞失效的主要原因，因此開展夾雜物對粉末冶金渦輪盤應力強度因子及裂紋萌生與擴展的影響具有重要意義。The counter - rotating dual - rotor system in aeroengines can reduce the influence of rotors ' gyroscopic moments on aircrafts, cut down the torque of cases and improve the flexibility of airplanes
摘要航空發動機採用反向旋轉的雙轉子系統，有助於減小轉子整體陀螺力矩對飛機的影響，降低機匣負荷，提高飛機機動性能。The interaction of fluid flow and heat transfer with flexible solid structures frequently results in deformation of structures in aero - engine. structural deformation has significant influence on characteristics of fluid flow and heat transfer, for example in the labyrinth seal
航空發動機中的許多部件存在著由於流體動力和傳熱引起的結構彈性變形，反過來，結構的變形又會直接導致流道的形狀的變化和其中的流動和傳熱特性的變化。( 3 ) using aga - fem to minimum the mass of an aeroengine case, the results indicate that the method we improved can be adopted to optimization of engine case and other engineering components
（ 3 ）將本文方法應用於某航空發動機機匣簡化結構的優化分析。分析表明，本文發展的方法對于機匣等工程構件有較好的適應能力。Taking ti alloy tc11 electron beam welded work - piece as research object, which is the conventional material of aero engine compressor blisc, the fatigue damage evolution law of fatigue damage action in the area of welded joint based on damage mechanics theory is analysed, and fatigue damage model, which macro - parameter and micro - damage characteristics are related, with fractal geometry - a new conception of modern mathematics is set up in this paper. it tries to research the measuring method of fatigue fracture fractal dimension and the relationship of fractal damage variable with fatigue life. it also sets up the welded joint fatigue damage fractal evolution equation
本課題以航空發動機壓氣機葉盤常用材料鈦合金（ tc11 ）電子束焊構件為研究對象，對焊接接頭的疲勞破壞行為，基於損傷力學理論分析其疲勞損傷演化規律，應用現代數學的新概念? ?分形幾何學理論，建立宏觀參量與細觀損傷特徵相聯系的疲勞損傷模型，研究疲勞斷口分維數測量方法以及分形損傷變量與疲勞壽命之間的關系，建立焊接接頭疲勞損傷分形演化方程。分享友人