Abstract: An improved ignitor plug for igniting fuel in a combustion chamber and a smart fuel supply system for ignitor plug applications.

Abstract: A transmission system for use with a microturbine engine that includes an input shaft operably coupled to the output shaft of the microturbine engine. The output shaft of the microturbine engine and the input shaft of the transmission system operate at a rotational speed in a range between 50,000 and 250,000 RPM with an output power between 200 and 5 HP. The transmission system includes a gear train having a first gear that interfaces to a second gear, the first and second gears employing teeth with opposite handed helix-angled surfaces that apply axial forces to the input shaft during both normal operation and start-up operations, which pushes the input shaft toward the output shaft of the microturbine engine. Preferably, the helix-angled surfaces on respective normal drive sides of the teeth produce an axial force during normal operation that will not be overcome with the axial force produced by the mass time acceleration of the first gear.

Abstract: A transmission system that is used in conjunction with a microturbine engine for propelling an aircraft body, such as a propeller-based fixed-wing aircraft or a rotor-based vertical lift aircraft, or for a wide variety of other applications. The output shaft of the microturbine engine preferably operates at a rotational speed in a range between 72,000 RPM and 150,000 RPM with an output power between 150 HP and 5 HP (and most preferably operates in an extended range between 50,000 RPM and 200,000 RPM with an output power between 200 HP and 5 HP). The two reduction stages provide a reduction ratio preferably having a value of at least 19, and most preferably greater than 24. The transmission system is of small-size preferably having a maximum diameter less than twelve inches.

Abstract: An improved glow plug for igniting fuel in a combustion chamber as well as a smart fuel supply system for glow plug applications.

Abstract: A transmission system that is used in conjunction with a microturbine engine for propelling an aircraft body, such as a propeller-based fixed-wing aircraft or a rotor-based vertical lift aircraft, or for a wide variety of other applications. The output shaft of the microturbine engine preferably operates at a rotational speed in a range between 72,000 RPM and 150,000 RPM with an output power between 150 HP and 5 HP (and most preferably operates in an extended range between 50,000 RPM and 200,000 RPM with an output power between 200 HP and 5 HP). The two reduction stages provide a reduction ratio preferably having a value of at least 19, and most preferably greater than 24. The transmission system is of small-size preferably having a maximum diameter less than twelve inches.

Abstract: A quantity of solid fuel is attached to the inside of the combustion chamber of the turbine. When the engine begins a starting sequence, a starter begins spinning the compressor and an air flow is pumped through the engine. The solid fuel is then heated by a heater element until the solid fuel begins to burn. The combustion of the solid fuel increases the temperature of the combustion chamber so that when, thereafter, an atomized or vaporized liquid fuel is injected, the temperature within the combustion chamber is sufficient to allow the liquid fuel to burn in a self-sustaining manner.

Abstract: A turbojet engine includes a housing having a forward inlet nozzle, an aft exhaust nozzle, a combustion chamber therebetween, a compressor between the inlet nozzle and the combustion chamber, and a turbine between the combustion chamber and the exhaust nozzle. A liquid fuel injector is provided to inject atomized or vaporized fuel into the chamber for combustion therein. In addition, a solid fuel is provided in the aft exhaust nozzle. The solid fuel may be used to assist the starting of the engine, particularly useful under adverse starting conditions. That is, when the compressor begins to spin up to pump air through the engine, the solid fuel in the exhaust nozzle is ignited by an igniter which begins to combust with the oxygen rich air introduced by the compressor. This combustion increases the temperature in the entire engine, such that when liquid fuel is injected in the combustion chamber, the temperature is sufficiently high to allow the liquid fuel to burn in a self-sustaining manner.