Abstract: The invention relates to a turbomachine assembly (1) comprising: a compressor (30), an isobaric combustion chamber (40), a piston engine (7) comprising: a shell (70), and a piston (72) movably mounted inside the shell (70) and defining with the shell (70) a variable-volume piston chamber (74), a turbine (50), and a differential transmission mechanism (8).

Abstract: An auxiliary power unit for an aircraft, having an engine core, a compressor having an outlet in fluid communication with the engine core inlet, a turbine section in fluid communication with the engine core outlet, and an excess air duct having a first end in fluid communication with the compressor outlet and a second end in fluid communication with a turbine inlet of the turbine section. The excess air duct defines a flow path between the compressor outlet and the turbine section separate from the engine core. The auxiliary power unit may include a generator in driving engagement with the engine core to provide electrical power for the aircraft. A method of providing compressed air and electrical power to an aircraft is also discussed.

Abstract: A propulsion and motion-transmission assembly (1), in particular for a rotary-wing aircraft, the assembly (1) comprising: a first motor-reducer assembly (2); and a second motor-reducer assembly (4), wherein the first and second motor-reducer assemblies (2, 4) are arranged for driving in rotation at least one rotor of a rotary-wing aircraft; and wherein each of said first and second motor-reducer assemblies (2, 4) comprises:—a mechanical differential (6, 24) including a first input shaft (8; 26), a second input shaft (10; 28) and an output shaft (12, 30); and—a first electric motor (14; 32) and a second electric motor (16; 34) connected, respectively, to said first and second input shafts (8, 10; 26, 28), the output shaft of each motor-reducer assembly being arranged for connection in rotation to a rotor of a rotary-wing aircraft.

Abstract: A serial fan module includes a first fan, a second fan and a plurality of guide elements. The first fan has a first frame body and a first impeller disposed within the first frame body. The second fan has a second frame body and a second impeller disposed within the second frame body. The guide elements are disposed between the first impeller and the second impeller, wherein the guide elements guide airflow from the first fan to the second fan. Each of the guide elements has an axial extended part and an inclined part and the inclined part meets the axial extended part at a camber angle. Each of the inclined part has an inner edge toward the first impeller and each of the axial extended part has an outer edge toward the second impeller.

Abstract: A propulsive fan system comprises a fan unit comprising a first stage array of rotatable blades upstream of a second stage array of rotatable blades. The first stage is coupled to a first drive means. The second stage is coupled to a second drive means. The first drive means is independently operable of the second drive means during operation of the fan system.

Abstract: A fan includes a first motor having a first rotor and a second motor having a second rotor which is rotationally connected to the first rotor. The fan further comprises a first impeller which, when driven by the first motor, rotates along a first direction and creates a main flow along a direction perpendicular to the periphery thereof and a tangential flow along the tangent thereof. The fan also includes a second impeller which, when driven by the second motor, rotates along the reverse direction of the first direction and impel the tangential flow to the direction perpendicular to the periphery of the first impeller.

Abstract: A connection structure is applied to a serial fan assembly, which includes an upstream fan and a downstream fan. The upstream fan and the downstream fan have different sizes. The connection structure connects the upstream fan and the downstream fan so that the upstream fan and the downstream fan are arranged in series. The connection structure has a housing, a base and a plurality of ribs for connecting the base, and the housing is formed with an air guiding passage and a chamber. The upstream fan or the downstream fan is accommodated in the chamber or the air guiding passage is located between the upstream fan and the downstream fan.

Abstract: A first motor rotates, in one of two rotating directions, the first impeller including a plurality of front blades in a suction opening portion of a housing. The second motor rotates, in the other rotating direction opposite to the one rotating direction, the second impeller including a plurality of rear blades in a discharge opening portion of the housing. A plurality of stationary blades are arranged between the first impeller and the second impeller in the housing. When the number of the front blades is N, that of the stationary blades is M, and that of the rear blades is P, their relationship is defined as N>P>M. A length L1 of the front blades measured in an axial direction is set longer than a length L2 of the rear blades measured in the axial direction.

Abstract: The present invention relates to a shock-absorbent structure of serially-connected fans. The serially-connected fans at least include two fan frames. A shock-absorbent element is disposed between the bonded surfaces of the fan frames and is made of a flexible material being shock-absorbent and damping. Therefore, when the fan rotor inside the fan frame rotates, the fundamental frequencies of two fan rotors are damped, and absorbed by the shock-absorbent element, thereby preventing the interaction of the fundamental frequencies from generating severe resonant effect and noise out of vibration and maintaining the optimized efficacy and the life span of the system.

Abstract: A first motor 25 rotates, in one of two rotating directions, the first impeller 7 including a plurality of front blades 28 in a suction opening portion 15 of a housing 59. The second motor 49 rotates, in the other rotating direction opposite to the one rotating direction, the second impeller 35 including a plurality of rear blades 51 in a discharge opening portion 57 of the housing 59. A plurality of stationary blades 61 are arranged between the first impeller 7 and the second impeller 35 in the housing 59. When the number of the front blades 28 is N, that of the stationary blades 61 is M, and that of the rear blades 51 is P, their relationship is defined as N>P>M. A length L1 of the front blades 28 measured in an axial direction is set longer than a length L2 of the rear blades 51 measured in the axial direction.

Abstract: A wind power system is provided including at least one generator fan having a front face and a rear face. The system also includes a first wind capturing device positioned proximate to the front face. The wind capturing device can be configured to capture wind to create a first pressure proximate to the front face that is greater than a second pressure proximate to the rear face. The pressure difference causes the captured wind to flow across the at least one generator fan from the front face to the rear face.

Abstract: In a rotary engine having rotating cylinders which burns a fuel which is not mixed with oil there is a real problem of centrifugal force form the rotating engine causing oil to flow into the combustion chambers. The disclosed rotary engine has oil reservoirs which are positioned radially outwardly from the pistons so that centrifugal force resulting from engine rotation tends to keep oil out of the combustion chambers.

Abstract: A twin engine, coaxial, dual-propeller propulsion system employing a unique transmission having two independent drive trains. The first of the two engines exclusively drives a first drive train, which in turn rotates a forward multi-bladed propeller assembly. The second engine exclusively drives a second drive train, which in turn rotates an aft multi-bladed propeller assembly. Thus, the propellers of this propulsion system, even though coaxial, are driven by separate engines. The propulsion system also enjoys the increased propulsive efficiency of a coaxial dual-propeller design as the first drive train rotates the forward propeller assembly in a first rotational direction and the second drive train rotates the aft propeller assembly in the opposite direction. Further, the propulsion system employs pitch change control mechanisms which independently control the respective pitch of the blades of the two propeller assemblies.

Abstract: A ship's drive with two counterturning propellers, the rear propeller of which is fastened to an inner shaft and the front propeller of which is fastened to the head end of a hollow shaft, which runs concentrically with the inner shaft. The hollow shaft is connected to a gearing and the inner shaft is connected to a propulsion unit. A gearwheel is disposed at the foot end of the hollow shaft which engages a further gearwheel which is fastened to an input shaft running parallel to the inner shaft. The input shaft can be connected with the output of a second engine.

Abstract: A cogwheel drive mechanism for driving at least one aircraft propeller or helicopter rotor through two transmissions, with two axially displaced transmission-connection shafts and at least one output shaft in the form of a propeller shaft or rotor shaft. The object is to ensure that at least one driven section will remain fully functional between one of the transmissions and one propeller or the other during any conceivable type of malfunction. There are two spatially separated individual drive mechanisms, each of which is accommodated in a separated housing that accommodates sections of one or both of the output shafts and each of which has one of the two connecting shafts.

Abstract: An aircraft drive system having two propellers, each of which is driven independently by a drive belt which is connected to a separate engine. The engines are mounted in cantilever fashion in a spaced relationship on a hollow sleeve. The sleeve is attached by a pair of spaced brackets to the frame of the aircraft. A shaft is rotatably telescopically mounted within the sleeve by bearings located on the ends of the sleeve. A pulley is fixedly mounted on one end of the shaft and is driven by one of the engines for rotating one of the propellers which is fixed on the other end of the shaft. Another pulley is rotatably mounted by bearings on the sleeve and is driven by a drive belt connected to the second engine. The second propeller is telescopically located about the sleeve adjacent the first propeller and is firmly connected to the second pulley which rotates said second propeller completely independent of the first propeller and in an opposite direction than the first propeller.