Propulsion module
AssigneeAllison Advanced Development Company
InventorVon David Baker
Life of this patent
Estimating the term…
Abstract
A propulsion module including a wave rotor detonation engine having a rotor with a plurality of fluid flow channels. The fluid flow channels extend between an inlet rotor plate, which has a pair of fixed inlet ports, and an outlet rotor plate, which has a pair of fixed outlet ports. The propulsion module includes a pair of inlet ducts have a stowed mode and a deployed mode. The pair of inlet ducts include a fluid flow passageway adapted to convey air to the pair of inlet ports. A fueling system is positioned prior to the inlet ports to deliver fuel into the air introduced through the pair of inlet ducts and into the pair of inlet ports. A pair of ignition chambers are disposed adjacent to the inlet rotor plate.
Claims24
A propulsion module, comprising:
- a wave rotor detonation engine having a rotor with a plurality of fluid flow channels extending between an inlet rotor plate having a pair of fixed inlet ports and an outlet rotor plate having a pair of fixed outlet ports;
- at least one inlet duct having a stowed mode and a deployed mode, said at least one inlet duct including a fluid flow passageway adapted for conveying air to said pair of inlet ports;
- a fueling system adapted to deliver a fuel into the air introduced through said at least one inlet duct and into said pair of inlet ports;
- an exhaust nozzle disposed in fluid communication with said pair of outlet ports;
- and
- at least one ignition chamber disposed adjacent said inlet rotor plate.
A propulsion module, comprising:
- a non-steady flow engine having at least a pair of inlet ports and at least a pair of outlet ports;
- an inlet duct having a stowed mode and a deployed mode, said inlet duct including a fluid flow passageway adapted for conveying air to said at least a pair of inlet port;
- a fueling system adapted to deliver a fuel into the air introduced through said inlet duct and into said at least a pair of inlet ports;
- an exhaust nozzle in fluid communication with said at least a pair of outlet ports;
- and
- an ignition chamber disposed adjacent each of said at least a pair of inlet ports.
A missile, comprising:
- a body member having a front end and a nozzle end;
- a wave rotor detonation engine positioned substantially within said body member, said wave rotor detonation engine having a rotor with a plurality of fluid flow channels extending between an inlet rotor plate having a pair of fixed inlet ports and an outlet rotor plate having a pair of fixed outlet ports;
- at least one inlet duct having a stowed mode wherein said at least one inlet duct is positioned substantially within said body member and a deployed mode wherein a substantial portion of said at least one inlet duct extends outwardly from said body member, said at least one inlet duct including a fluid flow passageway adapted for conveying air to said pair of inlet ports;
- a fueling system adapted to deliver a fuel into the air introduced through said at least one inlet duct and into said pair of inlet ports;
- an exhaust nozzle disposed in fluid communication with said pair of outlet ports;
- and
- at least one ignition chamber disposed adjacent said inlet rotor plate.
Dependencies are inferred from the claim text.