aero turbine 中文意思是什麼
aero turbine
解釋
航跡渦輪機-
Fracture analysis for rotor turbine blade in aero - engine
某發動機渦輪轉子葉片斷裂原因分析 -
In the matter - in - loop simulation experiment of aero - engine control system, the turbine outlet temperature, which characteristics with high and quick change, is hard to be simulated
航空發動機控制系統半物理模擬試驗中，渦輪出口氣體溫度高、變化快，難以模擬。 -
An interpolation program is used to convert the fluent result data to the ansys load data. it is a new method to analyze turbine tip clearance. in this paper, some research of the numerical computation of the tip clearance of aero - engine is done, the parametric method is used and the research on the flow, heat and structure integration analyses is accomplished
本文對渦輪機匣氣熱固一體化分析方法做了研究，通過編制了載荷轉換與施加程序，從氣熱計算模型中提取溫度場計算結果，並作為載荷加入到熱固耦合計算模型中，實現了高壓渦輪機匣的一體化計算分析，為實現渦輪葉尖間隙的氣熱固一體化分析打下了基礎。 -
Abstract : the paper presents the development and applications of thermal barrier coating, seal ( clearance control ) and wear resistance coating for aero gas turbine engine
文摘:介紹了在現代航空燃氣渦輪發動機上熱噴塗熱障、封嚴、耐磨塗層的開發應用實例。 -
The work of this thesis is financially supported by the aero fund project. the main purpose is to study the aerodynamics design technology of counter - turbine, to find the question differing from the aerodynamics design of general turbine, and to provide theoretical basis for development of aeroengine. first, the design method for the counter - turbine meridional flow is developed in the present thesis, and one 1 + 1 type counter - turbine is designed using this method
本論文的工作來源於航空科學基金項目，主要是研究對轉渦輪的氣動設計方法，並通過對對轉渦輪的氣動設計與分析，搞清對轉渦輪設計的關鍵問題、發現區別于常規渦輪設計的特殊性，為今後先進軍用戰斗機發動機燃氣渦輪設計與研製奠定理論基礎。 -
In this paper, the status quo of the tip clearance of aero - engine is surveyed, the theory and the method of the numerical computation of tip clearance are introduced, the simple tip clearance calculation program is modified and refined and the computation method of the turbine temperature field is improved
本文闡述了國內外航空發動機葉尖間隙的研究現狀，介紹了渦輪葉尖間隙計算的理論和方法。對渦輪葉尖間隙準二維計算程序作了修改和完善，改進渦輪部件溫度場的計算方法，增加了變量顯示/修改、程序控制和結果顯示界面，使軟體更加直觀，實用。 -
Finally, in order to solve the problems encountered in experiment, an improved design, including gas path, mechanism and controller design, is proposed. experiments are accomplished in the improved system platform, and the results demonstrate that the improved system can meet the requirement of simulating the turbine outlet temperature of aero - engine
最後，針對試驗中遇到的問題，從氣路部分、機械部分以及控制器三個方面對溫度模擬系統進行了改進設計，並在改進的系統平臺上進行了試驗，試驗結果表明改進后的系統能基本滿足對發動機渦輪出口溫度信號模擬需求。 -
The imperfection and fuzziness affecting the vibration reliability of structural components is analyzed, the concept of fuzzy safety state on vibration of structural components is developed, the fuzzy failure district of the resonant vibration of structural components and its membership function is constructed, the fuzzy failure district of the intensity is also constructed, the fuzzy model to assessment the vibration reliability of structural components is built and is applied to the vibration reliability assessment of the turbine blades and the compressor blades of the aero - engine
摘要分析影響構件振動可靠性的不確定性和模糊性因素，定義構件振動模糊安全狀態，構建構件振動的模糊共振失效區域及相應的隸屬函數、模糊強度失效區域及相應的隸屬函數，建立構件振動可靠性計算的模糊模型，並將其應用於某航空發動機壓氣機、渦輪葉片的振動可靠性計算。 -
It is crucial for cooling high temperature parts in aero - engines to master the rule of the flow field in turbine discs air cooling system
掌握渦輪盤腔冷卻系統內氣流的運動規律是對航空發動機高溫部件進行冷卻的關鍵。 -
Film cooling of the surface of a gas turbine blade was studied in a large - scale low - speed opening wind tunnel according to actual requirement of the design of aero - engine. the surface of a gas turbine blade was cooled by cylindrical holes in the experiment, with the hole number of fifteen in stator and eight in rotor
應航空發動機設計的要求，在大尺寸低速葉柵傳熱風洞中分別對發動機渦輪導向葉片和動葉表面的氣膜冷卻特性進行了研究，具體研究在不同氣膜孔出流時，在不同主流雷諾數和吹風比情況下葉片表面局部換熱系數的分佈規律。
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