This study investigates the direct impact of heat transfer on the thermodynamic performance of Micro Swing Rotor Engines(MSRE)through numerical analysis.To comprehensively address the influence of heat transfer,we emp...This study investigates the direct impact of heat transfer on the thermodynamic performance of Micro Swing Rotor Engines(MSRE)through numerical analysis.To comprehensively address the influence of heat transfer,we employ a refined thermodynamic simulation model,incorporating a regressive correlation formula,and introduce a fluid-thermal weak coupling method to yield practical solutions.The numerical analysis reveals that heat transfer has profound effects on the performance of MSRE.Specifically,the temperature cycling curve experiences significant alterations,resulting in an increase in cycle-residual mass by 72.6%and a decrease in intake mass by 10.55%at a working frequency of 100 Hz.The pressure cycling curve is primarily affected during the compression and expansion processes,leading to a substantial rise in pressure during compression(reaching1.055 MPa)while the contribution of combustion becomes less noticeable.Consequently,these changes increase engine power consumption during compression by 46.41%and reduce overall engine thermal efficiency by30.23%.Additionally,an increase of the inner wall temperature by 100 K leads to a linear reduction in engine power by 0.1 kW and thermal efficiency by 0.5%.To mitigate these challenges,we propose practical heat management strategies,such as applying heat insulating coatings.The study underscores the critical roles of heat transfer in MSRE operation and provides insights for optimizing its thermodynamic performance,achieving a potential improvement of up to 54.68%in power output and 12.79%in efficiency.展开更多
During the rotor assembly of aeroengines,the combined effect of blade mass moment variations and fixed tenon slot constraints makes single-phase rotor unbalance optimization strategies insufficient for real-world indu...During the rotor assembly of aeroengines,the combined effect of blade mass moment variations and fixed tenon slot constraints makes single-phase rotor unbalance optimization strategies insufficient for real-world industrial assembly scenarios.This often leads to excessive residual unbalance after assembly,resulting in engine vibrations and compromised operational stability.To address the lack of blade selection strategies and low qualification rates due to tenon slot constraints in industrial settings,this paper proposes a co-optimization method for blade selection and sequencing under industrial assembly constraints.A two-stage data-driven optimization framework is developed.In the first stage,a Dynamic Replacement Roulette Selection(DRWS)algorithm is introduced for global multi-set blade selection,improving blade utilization and avoiding selection failure caused by excessive moment dispersion.In the second stage,under fixed tenon slot constraints,blade sequencing is optimized using a Constrained Adaptive Genetic Algorithm(CAGA),effectively suppressing residual unbalance.Experimental results demonstrate that the proposed method achieves a blade utilization rate of 92.4%on 145 samples,with well-balanced group sets.Under tenon slot constraints,the residual unbalance is reduced from 58 g·mm and 94 g·mm(random assembly)to 7 g·mm and 10 g·mm,respectively.This study offers a novel solution and technical support for improving assembly precision and enabling intelligent decision-making in aeroengine rotor assembly lines.展开更多
Uncontained Engine Rotor Failure(UERF)can cause a catastrophic failure of an aircraft,and the quantitative assessment of the hazards related to UERF is a very important part of safety analysis.However,the procedure fo...Uncontained Engine Rotor Failure(UERF)can cause a catastrophic failure of an aircraft,and the quantitative assessment of the hazards related to UERF is a very important part of safety analysis.However,the procedure for hazard quantification of UERF recommended by the Federal Aviation Administration in advisory circular AC20-128A is cumbersome,as it involves building auxiliary lines and curve projections.To improve the efficiency and general applicability of the risk angle calculation,a boundary discretization method is developed that involves discretizing the geometry of the target part/structure into node points and calculating the risk angles numerically by iterating a particular algorithm over each node point.The improved efficiency and excellent accuracy for the developed algorithm was validated through a comparison with manual solutions for the hazard quantification of the engine nacelle structures of a passenger aircraft using the guidance in AC20-128A.To further demonstrate the applicability of the boundary discretization method,the proposed algorithm was used to examine the influence of the target size and the distance between the target and rotor on the hazard probability.展开更多
基金supported by the National Basic Research Program of China(Grant No.2014CB239602)the National Natural Science Foundation of China(Grant No.51176072)。
文摘This study investigates the direct impact of heat transfer on the thermodynamic performance of Micro Swing Rotor Engines(MSRE)through numerical analysis.To comprehensively address the influence of heat transfer,we employ a refined thermodynamic simulation model,incorporating a regressive correlation formula,and introduce a fluid-thermal weak coupling method to yield practical solutions.The numerical analysis reveals that heat transfer has profound effects on the performance of MSRE.Specifically,the temperature cycling curve experiences significant alterations,resulting in an increase in cycle-residual mass by 72.6%and a decrease in intake mass by 10.55%at a working frequency of 100 Hz.The pressure cycling curve is primarily affected during the compression and expansion processes,leading to a substantial rise in pressure during compression(reaching1.055 MPa)while the contribution of combustion becomes less noticeable.Consequently,these changes increase engine power consumption during compression by 46.41%and reduce overall engine thermal efficiency by30.23%.Additionally,an increase of the inner wall temperature by 100 K leads to a linear reduction in engine power by 0.1 kW and thermal efficiency by 0.5%.To mitigate these challenges,we propose practical heat management strategies,such as applying heat insulating coatings.The study underscores the critical roles of heat transfer in MSRE operation and provides insights for optimizing its thermodynamic performance,achieving a potential improvement of up to 54.68%in power output and 12.79%in efficiency.
基金supported by Basic Research Project for Young Students of the National Natural Science Foundation of China(grant number:524B2070)National Key Research and Development Program of China National Key R&D Program of China(2024YFF0726600,2024YFF0726601,2024YFF0726602,2024YFF0726604)+2 种基金Fundamental Research Funds for the Central UniversitiesNational Natural Science Foundation of China 52275525Postdoctoral Fellowship Program of CPSF under Grant Number BX20240476.
文摘During the rotor assembly of aeroengines,the combined effect of blade mass moment variations and fixed tenon slot constraints makes single-phase rotor unbalance optimization strategies insufficient for real-world industrial assembly scenarios.This often leads to excessive residual unbalance after assembly,resulting in engine vibrations and compromised operational stability.To address the lack of blade selection strategies and low qualification rates due to tenon slot constraints in industrial settings,this paper proposes a co-optimization method for blade selection and sequencing under industrial assembly constraints.A two-stage data-driven optimization framework is developed.In the first stage,a Dynamic Replacement Roulette Selection(DRWS)algorithm is introduced for global multi-set blade selection,improving blade utilization and avoiding selection failure caused by excessive moment dispersion.In the second stage,under fixed tenon slot constraints,blade sequencing is optimized using a Constrained Adaptive Genetic Algorithm(CAGA),effectively suppressing residual unbalance.Experimental results demonstrate that the proposed method achieves a blade utilization rate of 92.4%on 145 samples,with well-balanced group sets.Under tenon slot constraints,the residual unbalance is reduced from 58 g·mm and 94 g·mm(random assembly)to 7 g·mm and 10 g·mm,respectively.This study offers a novel solution and technical support for improving assembly precision and enabling intelligent decision-making in aeroengine rotor assembly lines.
基金supported by the National Natural Science Foundation of China(No.51706187)。
文摘Uncontained Engine Rotor Failure(UERF)can cause a catastrophic failure of an aircraft,and the quantitative assessment of the hazards related to UERF is a very important part of safety analysis.However,the procedure for hazard quantification of UERF recommended by the Federal Aviation Administration in advisory circular AC20-128A is cumbersome,as it involves building auxiliary lines and curve projections.To improve the efficiency and general applicability of the risk angle calculation,a boundary discretization method is developed that involves discretizing the geometry of the target part/structure into node points and calculating the risk angles numerically by iterating a particular algorithm over each node point.The improved efficiency and excellent accuracy for the developed algorithm was validated through a comparison with manual solutions for the hazard quantification of the engine nacelle structures of a passenger aircraft using the guidance in AC20-128A.To further demonstrate the applicability of the boundary discretization method,the proposed algorithm was used to examine the influence of the target size and the distance between the target and rotor on the hazard probability.
