Patent ID: 9650997
Date: 2017-05-16
CPC Classifications: F02K

Claim:
1. A rotary turbo rocket comprising: a forward facing air inlet; an aft facing exhaust nozzle; a turbojet engine having a longitudinal axis and comprising a compressor, a turbojet combustion chamber, and a turbine; a rotary rocket engine having a longitudinal axis and comprising a rotary rocket combustion chamber and two or more rocket outlets configured to release rocket combustion products toward the aft facing exhaust nozzle; a main shaft supporting rotating components of the turbojet and the rotary rocket engine; and a seal assembly configured to provide a first flow path between a fuel storage tank and a fuel feed line and said seal assembly configured to provide a second flow path between an oxidizer storage tank and an oxidizer feed line, said seal assembly positioned around a forward end of said main shaft in front of said compressor and behind said air inlet, wherein the turbojet engine and the rotary rocket engine are arranged coaxially with the turbojet engine positioned behind the air inlet and in front of the rotary rocket engine and the exhaust nozzle positioned behind the rotary rocket engine at the aft end of the rotary turbo rocket; wherein the rotary rocket engine is located at an aft end of the main shaft and the main shaft comprises said fuel feed line and said oxidizer feed line through which fuel and oxidizer are fed into the rotary rocket combustion chamber; and wherein said two or more rocket outlets each comprise a rocket nozzle positioned at a common radius from the main shaft and configured to provide a torque on a longitudinal axis of rotation of said rotary rocket such that the rotary rocket, in use, rotates said man shaft.