The invention relates to a manufacturing method of an engine thrust chamber. A rhenium-niobium integrated combustion chamber connected with a niobium ring is manufactured by a powder metallurgy near-net forming technology; iridium coatings are prepared on the inner and outer surfaces of the rhenium combustion chamber by an arc deposition method; a niobium and tungsten alloy extending section is prepared by a spinning process; the combustion chamber is connected with the extending section by an electronic beam welding process; a silicide coating on the surface of the extending section is prepared by a slurry sintering process; a metal oxide high-radiation coating is prepared on the outer surface of the combustion chamber by a plasma spraying technology; and a platinum-rhodium ring is prepared by the spinning technology and is assembled on the inner wall surface of the inlet end of the combustion chamber. Due to the novel design of the whole preparation process and the optimal design of technological methods and technological conditions of different preparation stages, the manufactured rhenium and iridium thrust chamber applied to an engine can obviously increase the allowable working temperature of the engine, and the aim for increasing the specific impulse of the engine is fulfilled; and a technical support is supplied to prolonging of the flying life of an aircraft, increase of an effective load or increase of a firing range.