compressor surge 中文意思是什麼

compressor surge 解釋
壓氣喘振
  • compressor : n. 1. 壓縮物。2. 壓縮器，壓氣機，壓榨器。3. 【解剖學】收縮肌，壓肌。
  • surge : n 大浪，波濤；波濤洶涌的大海；（人群、感情等的）洶涌，洋溢，起伏，高漲；〈詩〉海；【機械工程】波...
  1. At present, surge control method for centrifugal compressor being used is commonly by least - flow method. it can ’ t make compressor working within operating condition area, sometimes starts the surge control system earlier, which will waste energy sources and depress economy benefit. even, its control system commonly consists of simulation instrument, can ’ t modify the changing surge curve of compressor in time and can ’ t control nonlinear surge curve preferably

    目前，在用的離心壓縮機的防喘振方法一般採用最小流量法，它不能充分使壓縮機工作在其工況區，往往過早起動防喘振系統，浪費了能源，降低了經濟效益。且控制系統一般採用模擬儀表構成，在壓縮機的喘振線發生變化時不能及時修正，對非線性的喘振線不能較好的實施控制。
  2. On - line processing of faults of surge - proofing controller for co2 compressor

    控制系統防喘振控制器故障經驗總結
  3. Surge of centrifugal compressor and its prevent

    離心式壓縮機的喘振及預防
  4. Based on using the performance forecast model of centrifugal compressor, this paper the analyze is carried out on the performance forecast for centrifugal compressor and surge model of centrifugal compressor is established on its system. surge line of this system is obtained according to the performance similar principle. performance forecast software is compiled by using matlab at the same time

    本文在離心壓縮機性能預測模型的理論基礎上，對離心壓縮機進行性能預測分析，並建立系統的喘振模型，然後利用性能相似原理，得到離心壓縮機系統喘振線，同時利用matlab編制離心壓縮機性能預測軟體，應用於防喘振控制中，較好地解決了離心壓縮機因喘振現象而停機或為防止喘振現象的發生而過分加大迴流量，造成能源浪費的問題。
  5. Simulation results show that the surge line moved up - left relative to the original one and surge margin became larger when wet compression is used, which means wet compression can extend steady - operation regions of compressors and the si a - 02 gas turbine. at last, based on the moore - greitzer model surge and rotating stall of a compression system with wet compression is modeled with consideration of inlet evaporative cooling and compressor pressure rise when wet compression is used

    哈爾濱工程大學博士學位論文最後，本文在壓縮系統moors grei上zer模型的基礎上，考慮進口蒸發冷卻的作用和壓氣機濕壓縮過程的作用，推導出了濕壓縮系統喘振和旋轉失速的統一模型，該模型可以模擬系統發生喘振和旋轉失速時的瞬態響應以及噴水濕壓縮對系統瞬態響應的影響。
  6. Surge phenomenon is an instability flowing condition when centrifugal compressor working at low flux, it can make the compressor shut down, the production process interrupted, then bring us the loss of economy. further more, it can damage the compressor, make it broken and can even hurt people

    喘振現象是離心壓縮機工作在小流量時的不穩定流動狀態，它的出現輕則使壓縮機停機，中斷生產過程造成經濟損失;重則造成壓縮機葉片損壞，引起壓縮機設備報廢甚至造成人員傷害。
  7. This new technology changes from the traditional method by which the induced and compressor wheel separately are designed and produced to a new one by which the one - piece compressor is designed. on the basis of this new technology and the optimum blade profile, the performance of both the compressor and the turbocharger is largely improved. through the heating power calculation of the compressor, the analysis of the surge and the block of the compressor, the test - bed performance test of the turbocharger, the matching test of turbocharger and diesel engine, the propulsion test of the turbocharger on plateau condition, it is proved that the newly - designed compressor not only has high efficiency, but also improves the flow distribution in the high efficiency area so that the propulsion line can run through the high efficiency area

    主要內容包括：提出一種全新的壓氣機葉輪技術和概念，這種技術將傳統的導風輪和壓氣機分開設計、單獨加工改為整體設計、整體加工的單體葉輪；從增壓器與柴油機配機計算所得出的基本參數出發，通過對壓氣機進行熱力計算，確定壓氣機的基本結構參數；再對葉型以及葉輪輪廓與葉輪罩殼的配合間隙進行優化，對新設計的壓氣機進行喘振和堵塞分析；通過增壓器平臺性能試驗，驗證了新設計的壓氣機的性能水平得到了較大的提高，達到了提高增壓器的整體性能水平的目的；通過增壓器與柴油機配機試驗、以及增壓器用於高原條件下的牽引試驗，驗證了新設計的壓氣機不但具有高效率，還改善了高效率區的流量分佈，使牽引特性線貫穿高效率區。
  8. To meet the needs for wider surge margin of the turbofan engine, a new model was developed to predict the characteristics of the fan / high pressure compressor and turbine in this thesis. several ways, including, variable inlet guide vanes of the fan, variable guide vanes of the high pressure compressor, the variable inlet area ratio of the mixer and the nozzle areas, were presented to enlarge the surge margin of the turbofan engine. meanwhile, a method of combined variable geometries for optimizing controls of inlet guide vanes of the fan, guide vanes and the first two stators of high pressure compressor, area ratio of mixer and noz zle areas was established

    為了滿足下一代作戰飛機對推進系統的性能和穩定性要求，本文建立了壓縮系統特性和渦輪特性的新模型，並分別採用改變渦扇發動機風扇進口導流葉片、壓氣機導流葉片和前兩級靜葉片、混合室進口處內、外涵面積比和尾噴管面積，研究了其對發動機性能和穩定性的影響，進而得出了渦扇發動機變幾何擴穩的方法，為發動機變幾何擴穩研究打下理論基礎。
  9. The cause of turbine compressor surge was analyzed in air abruption set. a new method of pipeline technical innovation is put forward

    摘要分析了空分裝置中透平壓縮機產生喘振的原因，提出了管網系統技術改造方案。
  10. So under some situations, for example at the point of inception of surge or rotating stall, wet compression can be used to vanish surge and rotating stall, which will extend compressor steady operation region

    在一定的條件下，如在系統剛發生喘振或旋轉失速的時候，噴水濕壓縮可以用來消除喘振或旋轉失速，這有利於增大壓氣機的穩定運行范圍。
  11. We analyzed the centrifugal compressor ' s loading types, made certain the shift gears running work conditions of the centrifugal compressor, and putted forward the shift gears running energy - saving ratio calculational methods of centrifugal compressor, and discussed the centrifugal compressor ' s anti - surge conditions, and getted set the running ratating speed optimized mathematics model of centrifugal compressor

    分析了離心式壓縮機的負荷類型，確定了離心式壓縮機變速運行工況，提出了離心式壓縮機變速運行節能率計算方法，討論了離心式壓縮機的防喘振條件，建立了離心式壓縮機運行轉速優化的數學模型。
  12. I have shut down my no 3 engine due to compressor surge

    我已關掉第三號發動機，因壓縮器喘振。
  13. This thesis analyzed and evaluated the principle of vibration protection and surge control by introducing the air compressor train in pta plant, and vibration - proof steps were given

    摘要通過對pta裝置中大型空氣壓縮機組的介紹，對振動保護及喘振控制原理進行了分析並提出了保護措施。
  14. From the experimental, results it is observed that the adjustable inlet equipment can efficiently put off the occurrance of compressor surge and choke, and a wider range of flow in compressor working can be achieved

    結果表明，可調導風裝置能夠有效地延緩喘振和推遲阻塞的發生，擴大了壓氣機流量范圍。
  15. The performance of modern internal combustion engine for locomotives often depend on the improvement of the supercharge performance. as part of the main component of the compressor, the inlet turning tube will affect the performance, especially the surge margin, of the compressor directly

    現代內燃機車柴油機的功率和性能的提高在很大程度上取決于增壓器性能的提高，壓氣機進氣彎管作為增壓器的組成部分之一，直接影響壓氣機的性能和喘振裕度。
  16. 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
  17. 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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