The invention relates to an
assembly connection method and structure of a forced ignition type
aviation piston engine
combustion chamber, the structure comprises a cylinder body, a cylinder cover, a screw and a
gasket, the cylinder cover is provided with a taper hole corresponding to a threaded connection hole of the cylinder body, the screw comprises a threaded section, a taper rod section and a
screw head, and the screw is connected with the cylinder body at the threaded section. And meanwhile, the conical rod section is attached to the conical hole, so that the stress contact area between the screw and the cylinder cover is increased, additional torque formed by uneven
combustion stress of the cylinder cover on the screw can be decomposed through
conical surface fit, the axial tension borne by the cylindrical screw is reduced, and the difference of the expansion amount of each screw group on the cylinder cover is reduced. According to the method, through optimized and innovative design of a connecting
fastener and a matching part, on the basis of a
temperature difference assembly method, a cylinder cover is heated to 110 DEG C in advance, primary
assembly is completed in a near-vacuum environment, pre-tightening force is loaded step by step, secondary loading of screws is conducted after
heat balance is achieved between the connecting piece and the cylinder cover, and then the cylinder cover is assembled. And it is ensured that the pre-tightening force meets the design requirement, and then the assembling quality and sealing reliability are improved. The sealing performance of the
flange face of the
combustion chamber is improved, the
system assembling difficulty is reduced, the
thermal shock resistance of the structure is enhanced, the structure adapts to the offset
combustion chamber layout, and the safety and reliability of an engine are guaranteed.