Abstract
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.
Highlights
Because of the military’s single standard on fuel and the economy and availability for civil use, the compression ignition aviation piston engine has become a hot research topic [1]
Pilots want to use an economical and available fuel [4, 5]; all these have promoted the development of the aviation diesel engine
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
Summary
Because of the military’s single standard on fuel and the economy and availability for civil use, the compression ignition aviation piston engine has become a hot research topic [1]. Rebhi et al have studied the key components of the aircraft engine, such as the cylinder head; observed and analyzed fatigue cracks; confirmed that the crack origin was located at the most stressed area; and done a lot of research work on fatigue lifetime in terms of material properties of aircraft and engine components [8] These studies are of great significance for improving the life of engine components or the reliability of aircraft systems. Based on the deformation of the combined piston pin bore of a developing aviation piston heavy fuel engine as the research object, the paper analyzes the internal structure of the combined piston; the rule between the deformation of the piston pin bore and the position of internal thread is studied under the conditions of cylinder pressure, mechanical load, side force, and other multifield coupling. It can even be derived to a similar combined structure design to provide ideas for structural optimization design
Sign-in/Register to view highlights & summary Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
