초록 ▼

The rocket engine is fitted with an injection device comprising a single injection plate having a central portion that defines the end of the burn zone of the combustion chamber and that contains first propellant injectors having a high mixing ratio adapted to the conditions under which hot gases ar

The rocket engine is fitted with an injection device comprising a single injection plate having a central portion that defines the end of the burn zone of the combustion chamber and that contains first propellant injectors having a high mixing ratio adapted to the conditions under which hot gases are produced in the burn zone, and a peripheral portion in the form of a ring that defines the end of an annular cavity of a gas generator and that contain second propellant injectors having a low mixing ratio and adapted to the conditions under which hot gases are produced in the gas generator. The gas generator is thus integral with the combustion chamber and the annular cavity of the gas generator is separated from the burn zone of the combustion chamber by a cylindrical wall that extends axially perpendicularly to the injection plate and that is fixed thereto in sealed manner.

대표청구항 ▼

A liquid propellant rocket engine with parallel auxiliary flow, the engine comprising a combustion chamber defined by a main wall, an injection device for injecting first and second propellant components into the combustion chamber, at least one turbopump for feeding the injection device with the fi

A liquid propellant rocket engine with parallel auxiliary flow, the engine comprising a combustion chamber defined by a main wall, an injection device for injecting first and second propellant components into the combustion chamber, at least one turbopump for feeding the injection device with the first and second propellant components under determined pressure, and a gas generator for driving at least one turbine of said turbopump, wherein said injection device comprises a single injection plate including a central portion that defines the end of a burn zone of the combustion chamber and that contains first propellant injectors having a high mixing ratio adapted to the conditions of hot gas production in the burn zone of the combustion chamber, and a peripheral portion in the form of a ring that defines the end of an annular cavity of the gas generator and that contains second propellant injectors having a low mixing ratio adapted to the conditions of hot gas production in the gas generator, said gas generator thus being integrated in the combustion chamber with the annular cavity of the gas generator being separated from the burn zone of the combustion chamber by a cylindrical wall extending in an axial direction perpendicular to the injection plate and fixed to the injection plate in a sealed manner.