The invention discloses a combined type
combustion chamber for a two-
stroke high-power cross-ratio
aviation heavy oil
plunger engine. The combined type
combustion chamber comprises a cylinder body, a cylinder sleeve, a
cylinder head, a
plunger and a mono-block pump; the
cylinder head is fixed to the top of the cylinder body, the cylinder sleeve is fixed in the cylinder body, and the
plunger is arranged inside the cylinder sleeve; a concave pit A is designed in the middle of the top surface of the plunger, a concave pit B is designed in the middle of the bottom surface of the
cylinder head, and the concave pit A and the concave pit B are all shallow pits; the concave pit A, the concave pit B and the cylinder sleeve are combined together to form the combined type
combustion chamber; and the mono-block pump is fixed to the cylinder head, a
nozzle of the mono-block pump extends into the combined type
combustion chamber, and
nozzle holes of the
nozzle are located in the concave pit B. Two air inlets and one air outlet which are opposite to each other are designed and formed in the side wall of the lower portion of the cylinder body. According to the combined type
combustion chamber, the structure is compact, the
power to weight ratio is big, the combustion speed is high, and the maximum combustion pressure is small; the combustion temperature is low, and the air-exhausting quality is good; and the
scavenging form is
rotational flow scavenging, the charging loss is effectively lowered, and the volume efficiency is improved.