Abstract: The invention provides a high-speed rotor assembly for an overhung centrifugal compressor comprising a housing, a rotor component, an oil film damper and an impeller, which is adapted for connecting to a power output mechanism, wherein the rotor component is arranged inside the housing, and the oil film damper is disposed between the impeller and the rotor component, and the impeller is coupled to the rotor component. The rotor component further comprises a sleeve, a first bearing, a second bearing, a transmission shaft, a plurality of resilient elements and a spacer, wherein an end of the sleeve is connected to one of the circular rib by a screw while another end thereof is handing freely, and a oil film damper is disposed between the sleeve and another circular rib.

Abstract: A radial turbine wheel structure comprises a wheel disc, a plurality of full blades and a plurality of splitting blades. The splitting blades are disposed equidistantly around the wheel disc and are alternately disposed with the full blades. Wherein each of inlet shrouds, outlet shrouds, inlet hubs and outlet hubs separately has an included angle to a meridian plane of the wheel disc, and the full blades are related to the splitting blades in length. Hence, the radial turbine wheel is applied to the gas turbine generator set to increase the electricity generation efficiency of the gas turbine generator.

Abstract: A turbine motor for a pneumatic tool, comprising a casing, a rotor and an axis. Compressed air enters the casing through an inlet and is directed towards blades of the rotor in a radial direction, so that torque is exerted on the axis. The blades of the rotors are to a large part hit by compressed air, each for an extended time, so that high effectivity and good efficiency result, allowing for operation at high speed and under high load.

Abstract: The invention provides a high-speed rotor assembly for an overhung centrifugal compressor comprising a housing, a rotor component, an oil film damper and an impeller, which is adapted for connecting to a power output mechanism, wherein the rotor component is arranged inside the housing, and the oil film damper is disposed between the impeller and the rotor component, and the impeller is coupled to the rotor component. The rotor component further comprises a sleeve, a first bearing, a second bearing, a transmission shaft, a plurality of resilient elements and a spacer, wherein an end of the sleeve is connected to one of the circular rib by a screw while another end thereof is handing freely, and a oil film damper is disposed between the sleeve and another circular rib.

Abstract: A recuperated gas turbine engine. The gas turbine engine includes a heat exchanger, and gas turbine (including compressor, can-type combustor and turbine). The heat exchanger includes a compressed air passageway and a turbine exhaust gas passageway adjacent to each other within the casing which extend spirally throughout the heat exchanger and towards an inner cylindrical chamber in which the combustor is positioned approximately to the center of the casing. Improved engine fuel efficiency is achieved by preheating the compressed air before it reaches the combustor with the higher-temperature exhaust gas. A can-type combustor is used for alleviating heat-dissipation issues to improve efficiency of the combustion. A concentric back-to-back rotor arrangement significantly shortens the length of a conventional engine turbine rotor which improves on the operational stability of a gas turbine engine.

Abstract: A recuperated gas turbine engine is disclosed, comprising: a heat exchanger, and gas turbine (including compressor, can-type combustor and turbine); wherein, said heat exchanger comprises a compressed air passageway and a turbine exhaust gas passageway adjacent to each other within the casing which extend spirally throughout said heat exchanger and towards an inner cylindrical chamber in which said combustor is positioned approximately to the center of said casing. Improved engine fuel efficiency is achieved by preheating the compressed air before it reaches the combustor with the higher-temperature exhaust gas. A can-type combustor is used for alleviating heat-dissipation issues to improve efficiency of the combustion. A concentric back-to-back rotor arrangement significantly shortens the length of a conventional engine turbine rotor which improves on the operational stability of a gas turbine engine.

Abstract: An engine core structure for a gas turbine engine includes an outer annular shaft body, a turbine rotor body, turbine rotor blades radially connected between the outer annular shaft body and the turbine rotor body to hold the turbine rotor body in the rear section of the outer annular shaft body, the outer annular shaft body including slots through which compressed air passes in a radially inward direction, and a can type combustor mounted in a receiving clamber inside the outer annular shaft body to enlarge the diameter of the core shaft, to avoid vibration due to resonance, to save space, to eliminate dissipation of heat, and to improve the thermal efficiency of the gas turbine engine.

Abstract: An engine core rotor shaft structure for gas turbine engine is disclosed, which includes an outer annular shaft body, an inner annular shaft body, high pressure turbine (HPT) rotor blades radially connected between the outer annular shaft body and the inner annular shaft body to hold the inner annular shaft body in the rear section of the outer annular shaft body, and a can type combustor mounted in a receiving chamber inside the outer annular shaft body to enlarge the diameter of the core shaft, to avoid vibration due to resonance, to save space occupation, to eliminate dissipation of heat, and to improve the thermal efficiency of the gas turbine engine.

Abstract: Disclosed is a method and device for automatic dynamic balancing operations on machine lines so as to compensate unbalance in a rotor. Vibration signals of the rotor obtained by a transducer and revolution signals generated by a revolution detector in reaction to the rotor during rotation are fed into a band pass filter and amplifier. The processed signals are then converted into digital signals by means of a digital dynamic balancing close-loop controller. The value and location of unbalance present in the rotor are calculated by a calculating unit. Based on the unbalance value and the speed of revolution of the rotor, whether a suitable amount of fluid is needed to be injected into compensation chambers in the rotor, which is coaxial with the rotor, to eliminate the unbalance of the rotor can be determined. This balancing operation is repeated automatically until the unbalance value is less than a predetermined tolerance value.