Patent ID: 11970996
Assignee: SPECIAL AEROSPACE SERVICES, LLC
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 15:
16. A rocket engine comprising:
a fuel supply line configured to supply a fuel;
an oxidizer supply line configured to supply an oxidizer, the oxidizer supply line comprising a set of partial oxidizer supply lines;
a turbine mounted to a turbine shaft along a longitudinal centerline of the rocket engine, the turbine configured to rotate with the turbine shaft about the longitudinal centerline;
a main combustion chamber comprising a main combustion chamber injector head, the main combustion chamber in fluid communication with the turbine and in fluid communication with at least one of the set of partial oxidizer supply lines;
a flow collimator positioned longitudinally proximal to the main combustion chamber injector head, the flow collimator comprising a set of apertures positioned longitudinally distal to the gas duct, the flow collimator in fluid communication with a gas duct and with the main combustion chamber; and
a preburner combustion chamber comprising a preburner injector head;
wherein:
the preburner injector head injects the fuel with the oxidizer to create preburner combustion exhaust products which drive the turbine about the turbine shaft; and
the main combustion chamber injector head injects the preburner combustion exhaust products received from the turbine with the oxidizer to produce a rocket engine thrust.