Disclosed is a rotary drive apparatus comprising a housing, within which is located a first rotor and second rotor, the first rotor being rotatable about a first axis and having a rotor element projecting radially therefrom, and a second rotor being rotatable about a second axis parallel to the first axis and in a direction opposite to the first rotor, the second rotor comprising a recess able to receive the rotor element, wherein the first rotor and the second rotor and housing define a chamber around the first rotor through which the rotor element passes, the chamber having an inlet and an outlet through which a fluid can enter and exit the chamber.

Rotary vane internal combustion engine comprises of two side-by-side rotors, placed in a cylindrical housing, wherein each rotor has at least two radial vanes rigidly attached to the rotor that form chambers for intake, compression, combustion, and exhaust. Each rotor alternately engages with a shaft by overrunning one-way clutches and is held from turning back, through the damper, mounted on a corresponding flywheel and forming a part of the flywheel assembly, which is rigidly attached on the shaft. The assembled rotors from the outside are rigidly closed by flanges on each of which is mounted at least one blade. The blades are positioned into formed cavities between the rotors and caps of the housing, thereby forming two cooling cavities through which coolant circulates around rotors through openings in the housing and through longitudinal grooves in the shaft. On the vanes are mounted cylindrical and conical seals, which remove the need for lubrication.

Methods and systems are provided for a ducted fuel injector. In one example, the ducted fuel injector comprises a plurality of passages, with at least one of the passages configured to receive an oxygen poor gas from a reservoir or an adjacent cylinder to decrease a likelihood of pre-ignition in the duct.

An internal combustion engine comprises a plurality of engine units (50A-50C), each having a working space (11), in which two rotary pistons (20, 30) are arranged so as mesh with each other and thereby divide the working space (11) into an inflow region (12) and an outflow region (13). Each engine unit comprises a closable inlet opening (62A-62C) to the inflow region (12) and a closable exhaust gas outlet opening (64A-64C). The internal combustion engine further comprises a feed-line pipe (60) to the inlet openings (62A-62C) and an exhaust gas collection pipe (66) connected to the exhaust gas outlet openings (64A-64C), so that the engine units (50A-50C) are connected in parallel with each other. The internal combustion engine further comprises exhaust gas lines (63A, 63B) which connect the engine units (50A, 50B) with each other in series. In dependence upon a desired power output, a control device (70) operates some of the engine units (50B, 50C) either as internal combustion engines, wherein the respective inlet opening (62B-62C) is opened, or as expansion engines, wherein respective inlet opening (62B-62C) remains closed and the respective rotary pistons (20, 30) are instead driven by exhaust gas flowing in via the respective exhaust gas line (63A, 63B).

An internal combustion engine comprises a plurality of engine units (50A-50C), each having a working space (11), in which two rotary pistons (20, 30) are arranged so as mesh with each other and thereby divide the working space (11) into an inflow region (12) and an outflow region (13). Each engine unit comprises a closable inlet opening (62A-62C) to the inflow region (12) and a closable exhaust gas outlet opening (64A-64C). The internal combustion engine further comprises a feed-line pipe (60) to the inlet openings (62A-62C) and an exhaust gas collection pipe (66) connected to the exhaust gas outlet openings (64A-64C), so that the engine units (50A-50C) are connected in parallel with each other. The internal combustion engine further comprises exhaust gas lines (63A, 63B) which connect the engine units (50A, 50B) with each other in series. In dependence upon a desired power output, a control device (70) operates some of the engine units (50B, 50C) either as internal combustion engines, wherein the respective inlet opening (62B-62C) is opened, or as expansion engines, wherein respective inlet opening (62B-62C) remains closed and the respective rotary pistons (20, 30) are instead driven by exhaust gas flowing in via the respective exhaust gas line (63A, 63B).

An internal combustion rotary engine is provided for producing mechanical torque. The engine includes an annular planar housing, a rotor, sparkplugs, flap valves, an axial shaft and fore-and-aft covers. The housing includes a quadrilateral symmetry including a substantially circular annulus flanked by first and second cavities. The rotor has a cam block sandwiched between fore and aft circular wings. The sparkplugs are respectively accessible to the second cavities. The flap valves rock within the respective cavities and within the cam block. Each valve includes indents to pass around the wings. The fuel intake provides fuel to the cavities. The axial shaft rotates the rotor within the housing. Covers, each having a center orifice and a pair of ports exposed to ambient and respectively adjacent the first and second cavities. The wings intermittently block at least one port while the rotor rotates.

An internal combustion rotary engine is provided for producing mechanical torque. The engine includes an annular planar housing, a rotor, sparkplugs, flap valves, an axial shaft and fore-and-aft covers. The housing includes a quadrilateral symmetry including a substantially circular annulus flanked by first and second cavities. The rotor has a cam block sandwiched between fore and aft circular wings. The sparkplugs are respectively accessible to the second cavities. The flap valves rock within the respective cavities and within the cam block. Each valve includes indents to pass around the wings. The fuel intake provides fuel to the cavities. The axial shaft rotates the rotor within the housing. Covers, each having a center orifice and a pair of ports exposed to ambient and respectively adjacent the first and second cavities. The wings intermittently block at least one port while the rotor rotates.

This patent discloses thrust vectoring ignition chamber engine in which ignition chamber is an annular cylinder having nozzles mounted such that during fuel suction phase they are sealed and during ignition of fuel they are unsealed so that hot jets of ignited fuel escaping through nozzles cause coupled rotatory motion on the ignition chamber. Engine uses specially designed dwell barrel cam mechanism for two phase suction and compression of fuel which facilitates the separation of fuel valve from ignition chamber. Flywheel mounted on extension of ignition chamber functions as output of the engine. Timing of electrically controlled nozzle seal and fuel valve can be adjusted so that each half rotation of flywheel completes three phases namely fuel/air suction, compression and combustion, instead of two rotations as required in engine according to prior art. This engine can give improved power boost by firing for every half revolution.

This patent discloses thrust vectoring ignition chamber engine in which ignition chamber is an annular cylinder having nozzles mounted such that during fuel suction phase they are sealed and during ignition of fuel they are unsealed so that hot jets of ignited fuel escaping through nozzles cause coupled rotatory motion on the ignition chamber. Engine uses specially designed dwell barrel cam mechanism for two phase suction and compression of fuel which facilitates the separation of fuel valve from ignition chamber. Flywheel mounted on extension of ignition chamber functions as output of the engine. Timing of electrically controlled nozzle seal and fuel valve can be adjusted so that each half rotation of flywheel completes three phases namely fuel/air suction, compression and combustion, instead of two rotations as required in engine according to prior art. This engine can give improved power boost by firing for every half revolution.

A method of operating an aircraft engine of an aircraft, the aircraft engine having a common-rail fuel injection system for injecting fuel into a combustion chamber of the aircraft engine, including: pressurizing fuel for circulation through the common-rail injection system; circulating a portion of the pressurized fuel through a motive flow inlet of an ejector pump; and entraining a flow through the ejector pump with the portion of the pressurized fuel circulating through the motive flow inlet.