軸流壓氣機 的英文怎麼說

中文拼音 [zhóuliúyāqìjī]
軸流壓氣機 英文
axial-flow compressor
  • 軸 : 軸Ⅰ名詞1. （圓柱形的零件） axle; shaft 2. （對稱部分的直線） axis 3. （圓柱形的纏繞器物） roller; spool Ⅱ量詞（用於纏在軸上的線以及裝裱帶軸子的字畫）
  • 流 : Ⅰ動1 （液體移動; 流動） flow 2 （移動不定） drift; move; wander 3 （流傳; 傳播） spread 4 （向壞...
  • 壓 : 壓構詞成分。
  • 氣 : Ⅰ名詞1 （氣體） gas 2 （空氣） air 3 （氣息） breath 4 （自然界冷熱陰晴等現象） weather 5 （氣味...
  • 機 : machineengine
  1. Exploring mechanism of stall margin enhancement of subsonic axial - flow compressor through steady micro tip injection

    定常微量噴氣提高軸流壓氣機穩定工作裕度機理探討
  2. In order to investigate the unsteady flow frequency domain performances of an axial flow compressor at different mass flow, rotating speed and blade row spacing, plus inlet flow distortion, and considering aerodynamic characteristics and stability of the compressor, the low speed research compressor ( lsc ) at college of energy and power in nuaa is used to carry out the experiment studies. a large amount of test data has been gained through dynamic pressure transducers embedded in the stator blades at the tip, middle and hub section, then fast fourier transform algorithm ( fft ) is applied to calculate the frequency data

    為探討軸流壓氣機在工作流量、工作轉速及動?靜葉排軸向間距變化時的葉片排流場非定常頻譜特性變化規律，並耦合進氣畸變的影響，同時與壓氣機氣動性能和氣動穩定性相關聯，作者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，採取在靜子葉片表面埋入動態壓力傳感器的實驗方法，對葉尖、葉中和葉根三個截面的動態壓力進行了測量，獲得了大量的可靠的實驗數據。
  3. The effect of leakage flow due to the upstream hub axial gap on the rotor performance and the mechanism of interaction between the hub leakage flow and the rotor blade passage flow were studied based on the numerical simulations of the flow fields of a transonic compressor rotor with upstream hub leakage

    摘要為研究壓氣機轉子上游葉根軸向間隙泄漏流對轉子性能的影響程度以及泄漏流與轉子流場之間的相互作用機制，對帶有葉根泄漏流的跨聲壓氣機轉子流場進行了數值模擬。
  4. Experimental study of small perturbation induced rotating stall in axial flow compressor

    軸流壓氣機小擾動誘發旋轉失速的試驗研究
  5. Experimental and numerical investigation of stepped tip gap effects on an axial - flow compressor

    梯狀間隙結構對軸流壓氣機影響的試驗與數值模擬
  6. Analysis on the aerodynamic behaviors of the swept leading edge shocks in high load axial compressors

    軸流壓氣機掠形前緣激波動力學效應的模型分析
  7. Experimental research of an axial flow compressor performance with stepped tip gap casing configuration

    梯狀尖部間隙機匣處理對軸流壓氣機性能影響的實驗研究
  8. The effect of tip injection on the performance of an axial - flow compressor was performed numerically

    採用數值模擬方法研究了頂部噴氣對某軸流壓氣機氣動性能的影響。
  9. On the basis of analyzing the aerodynamical property and the construction of usual axial fan, the aerodynamical property and the construction of contra - rotating axial local fan are studied in the paper. moreover, author has designed a kind of contra - rotating local fan, which has the characters of low noise, high efficiency, well aerodynamical performance, optimum structure, and large power

    本文在分析了普通軸流式通風機的氣動力特徵和結構的基礎上，研究了對旋式軸流通風機的氣動力特性和結構特點，設計並製造出了一種風量大，風壓高，噪聲低，效率高，氣動性能好，體積小，結構新穎的2 30kw新型大功率對旋式軸流局部通風機樣機。
  10. In this paper, the performance of a multi - spool axial - flow compressor with a fan during operation with water ingestion is investigated

    本文主要研究了多級軸流風扇壓氣機在有水或者其它液相注入時的性能特性。
  11. The multi - stage axial compressor performance was measured using a streamline curvature method based on two - dimension ( axisymmetric ) mathematical model

    摘要採用二維（軸對稱）數學模型，應用流線曲率法求解多級軸流壓氣機特性。
  12. 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。
  13. By comparing the calculated results and test data for a multi - stage axial compressor, this method demonstrates that it could assist in predicting the characteristics of multistage axial compressor and spanwise parameter distribution under off design working conditions

    對一臺多級軸流壓氣機的計算結果與試驗數據的對比分析表明，該方法能較好地預測多級軸流壓氣機的特性和非設計工況下級間參數的分佈。
  14. The radial, circumferential and axial distributions of static pressure amplitude under post - stall conditions are measured and compared. the experimental results have proved the feasibility of using one - dimensional model to analyze the post - stall behavior and recoverability of compression systems. at the same time, the results of experiment have provided the first - hand data for analyzing and calculating vibrating response of blades under post - stall conditions

    以單級軸流壓氣機實驗器為對象，研製了兩種型式的靜壓動態探針?梳形針和圓盤針，詳細測量了過失速狀態下流道中壓力沿徑向、周向和軸向分佈，驗證了用一維模型分析壓氣機過失速性能和失速可恢復性的可信度，同時為過失速狀態下葉片的振動響應分析計算提供了第一手實驗數據。
  15. Nasa - 37 transonic and nwpu - 1 subsonic rotors are calculated by using this program. results of calculation indicates that this program can admirably simulate rotor rows flow in axial compressors and distinguish passage shock, leakage vortex path and separation of boundary layer

    用該程序分別計算了nasa - 37跨音速轉子和nwpu - 1亞音速轉子，計算結果表明本文建立的孤立轉子程序能夠較好的模擬軸流壓氣機葉片排內流動情況，能夠有效的捕捉通道激波和間隙泄漏渦軌跡以及葉片附面層的分離。
  16. Technical specification for construction of fccu axial flow compressor - flue gas turbine trains

    催化裂化裝置軸流壓縮機-煙氣輪機機組施工技術規程
  17. The unsteady surface pressures on the rotor blades of a single - stage low - speed axial compressor were measured by means of mounting micro - sensors on the surface the blades

    摘要為了研究上游葉片尾跡對軸流壓氣機轉子葉片非定常表面壓力的影響，採用在葉片表面埋設微型壓力傳感器的方法，測量了一個單級低速軸流壓氣機轉子葉片的非定常壓力分佈。
  18. By using a reynolds - averaged two - dimensional computation, the effect of upstream wake on unsteady separated flow field of downstream adjacent vanes was investigated in low - speed axial compressor

    摘要利用二維數值模擬研究了低速軸流壓氣機上游尾跡對下游相鄰葉排的非定常分離流場的影響。
  19. Abstract : concerning the models for discribing aerodynamic stability of axial flow compressor, the original model is one - dimensional, and it is reasonable for the onset of surge only. for the onset of rotating stall, there are just some two - dimensional models at published literatures. a three - dimensional aerodynamic of compressor has been presented in this paper. an aerodynamic stability model concerning radial disturbance of compressor is presented. the calculated results show that the occurrence of radial disturbance is related to the axial velocity disturbance, which has important effect on aerodynamic stability of compressor. the position of onset of stall, in blade tip or hub, is dependent upon the characteristics of blade element. the comparisons of calculated results predicted by 2d and 3d aerodynamic stability model have also been made in this paper

    文摘:軸流壓氣機的氣動穩定性模型，最初為一維模型，僅適用於描述喘振發作.對于旋轉失速發作，在公開文獻中有一些二維模型發表.本文提出了一類考慮壓氣機徑向擾動對失速影響的新的氣動穩定性模型.計算結果表明壓氣機的軸向擾動往往隨著徑向擾動的產生，徑向擾動的強度影響壓氣機的氣動穩定性，在葉尖還是葉根首先產生失速與壓氣機基元葉柵特性密切相關.本文對軸流壓氣機二維和三維氣動穩定性模型的計算結果進行了對比分析
  20. Concerning the models for discribing aerodynamic stability of axial flow compressor, the original model is one - dimensional, and it is reasonable for the onset of surge only. for the onset of rotating stall, there are just some two - dimensional models at published literatures. a three - dimensional aerodynamic of compressor has been presented in this paper. an aerodynamic stability model concerning radial disturbance of compressor is presented. the calculated results show that the occurrence of radial disturbance is related to the axial velocity disturbance, which has important effect on aerodynamic stability of compressor. the position of onset of stall, in blade tip or hub, is dependent upon the characteristics of blade element. the comparisons of calculated results predicted by 2d and 3d aerodynamic stability model have also been made in this paper

    軸流壓氣機的氣動穩定性模型，最初為一維模型，僅適用於描述喘振發作.對于旋轉失速發作，在公開文獻中有一些二維模型發表.本文提出了一類考慮壓氣機徑向擾動對失速影響的新的氣動穩定性模型.計算結果表明壓氣機的軸向擾動往往隨著徑向擾動的產生，徑向擾動的強度影響壓氣機的氣動穩定性，在葉尖還是葉根首先產生失速與壓氣機基元葉柵特性密切相關.本文對軸流壓氣機二維和三維氣動穩定性模型的計算結果進行了對比分析
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