High cycle fatigue analysis for oil pan of piston aviation kerosene engine

Pan, Zhongjian; He, Qinghua

doi:10.1016/j.engfailanal.2014.12.009

Cited by 13 publications

(7 citation statements)

References 12 publications

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“…Mechanical failures of different aircraft structural components are common case in practice [1][2][3][4][5][6][7][8][9][10][11][12]. There are numerous causes of failure such as corrosion, porosity, high cycle fatigue and the like.…”

Section: Introductionmentioning

confidence: 99%

Further investigation of the repetitive failure in an aircraft engine cylinder head - Mechanical properties of Aluminum alloy 242.0

Vučetić

Jovičić

Krstic

et al. 2020

mech

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Aluminum alloys are widely used in military and aviation industry due to their properties such as low density and high strength. During the aircraft operation there are mechanical failures of various structural components caused by numerous mechanisms such as corrosion, material defects, high cycle fatigue and the like. One of the frequent mechanical failures on air-cooled piston engines is the cylinder head cracking. This paper is the continuation a comprehensive research of the Lycoming IO-360-B1F aircraft cylinder head failure. The failure of this type has already occurred during flight and about 50 failures like this have been registered from around the world, some of them with a fatal outcome and therefore require detailed research. The paper consists of machining of the tested specimens and their testing at many different locations and in many different laboratories throughout Bosnia and Herzegovina, Serbia and Slovenia. This paper is based on a research that includes the experimental analysis of mechanical properties of Aluminum alloy 242.0 which is a constituent material of the cylinder head of the Lycoming IO-360-B1F aircraft engine on which a crack appeared. Based on chemical, metallographic, static and dynamic experimental tests of the material properties, Aluminum alloy 242.0 static and fatigue properties were obtained, S-N curve was formed and endurance limit was determined. Results of numerical simulations of experiments, confirmed by experimental results, were performed to make numerical procedures reliable due to further research. The results of the research are planned to be implemented in numerical modeling of the cylinder assembly stress-strain state under workload and in further numerical research of Lycoming IO-360-B1F cylinder assembly integrity assessment.

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Section: Introductionmentioning

confidence: 99%

Further investigation of the repetitive failure in an aircraft engine cylinder head - Mechanical properties of Aluminum alloy 242.0

Vučetić

Jovičić

Krstic

et al. 2020

mech

View full text Add to dashboard Cite

show abstract

“…Pilots want to use an economical and available fuel [4,5]; all these have promoted the development of the aviation diesel engine. At present, a general aircraft mainly uses aviation gasoline engines, compression ignition aviation heavy fuel engines are used less, and there are very few reports on their research [6,7]. To reduce the weight of the piston, lower the piston inertia force during the reciprocating process, and improve the power-weight ratio, some aviation piston compression ignition engines adopt a combined piston with the head made of high strength steel and piston skirt of aluminum alloy.…”

Section: Introductionmentioning

confidence: 99%

Failure Analysis of the Pin Bore of the Combined Piston for the Aero Engine

Pan

Guo

2019

International Journal of Aerospace Engineering

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The combined piston can be used in an aero piston heavy fuel engine because of its light weight, so as to reduce the reciprocating inertia force and improve the engine power-weight ratio. However, the pin bore of the combined piston is prone to deform leading to the failure of the piston. Based on the structure of the piston, the stress of the piston under thermomechanical coupling is analyzed, the temperature field of the piston is determined by experiments, and the deformation rule of the piston pin bore under the thermomechanical coupling is summarized. A design scheme is proposed to change the position of the thread connection between the piston crown and the piston head. Under the same conditions, the deformation of the piston pin bore of the original scheme and the new scheme is analyzed. The results show that together with the changing of the connection thread between the piston crown and the piston head, the deformation of the piston pin bore decreases by 60 μm and the deformation of the piston pin bore is controlled. The test results show that the deformation of the pin bore is within the acceptable range, which proves the effectiveness of the improved scheme.

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“…There is very little research on emissions of aviation heavy oil piston engine. So far, the manufacturers who have obtained type certifications are Thielert in Germany, Continental in United States, Austro in Germany, SMA in France [15], the developing DeltaHawk in the U.S., and Wilksch in Britain [16][17][18][19]. Emission control indicators have been formed on aviation turbine engines; Federal Aviation Administration (FAA) and European Aviation Safety Agency (EASA) have not made requirements for emissions when collecting airworthiness certificates of aviation piston engines.…”

Section: Introductionmentioning

confidence: 99%

Regular Analysis of Aero-Diesel Piston Engine between Combustion Chamber Size and Emission

Pan

Cheng

2019

International Journal of Aerospace Engineering

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The emission of aero-engines has been a focused issue, studying the regular of combustion chamber size on engine emission performance, with an aviation diesel piston engine as the object of study; the numerical model of diesel combustion spray and emission model are analyzed; and the dynamics grid of the combustion chamber is meshed by FIRE software, analyzing the relationship between the reentrant diameter, the maximum depth of the combustion chamber, and the emission generation, comparing the NOx and soot emissions under different combustion chamber sizes. The results show that reducing appropriately the reentrant-max diameter ratio and max diameter-max depth ratio of the combustion chamber can reduce emissions when maintaining the same compression ratio by adjusting the mid-depth. Modifying the geometry parameters of the combustion chamber to verify regularity, it was found that engine NOx emission decreased by 28% and soot emission decreased by 3.6% when changing the size, which verified the correctness of regular analysis.

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High cycle fatigue analysis for oil pan of piston aviation kerosene engine

Cited by 13 publications

References 12 publications

Further investigation of the repetitive failure in an aircraft engine cylinder head - Mechanical properties of Aluminum alloy 242.0

Further investigation of the repetitive failure in an aircraft engine cylinder head - Mechanical properties of Aluminum alloy 242.0

Failure Analysis of the Pin Bore of the Combined Piston for the Aero Engine

Regular Analysis of Aero-Diesel Piston Engine between Combustion Chamber Size and Emission

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