An aerofoil body for a gas turbine engine is provided. The aerofoil body has leading and trailing edge portions, wherein one of the leading and trailing edge portions is a morphable edge portion having a composite layer structure. The aerofoil body further has a non-morphing central portion which forms pressure and suction surfaces of the aerofoil body between the leading and trailing edge portions. The composite layer structure includes a return spring, one or more shape memory alloy layers, and a flexible cover for the return spring and the one or more shape memory alloy layers. The flexible cover defines pressure and suction surfaces of the aerofoil body at the morphable edge portion. The one or more shape memory alloy layers are electrically heatable to deform the layers against the resistance of the return spring, and thereby alter the pitch of the aerofoil body at the morphable edge portion.

A blower and a method for decreasing eddy noise are provided. The blower includes a fan frame, a fan wheel, at least one induction element and a coil. The fan frame has in inlet and an outlet. The fan wheel is disposed in the fan frame and has a wheel hub and a plurality of fan blades connected to periphery of the wheel hub. The induction elements are fixed to the corresponding fan blades, the coil is disposed on the fan frame for driving the at least one induction element, such that the fan blade corresponding to the induction element swing back and forth to generate a vibration sound, and the vibration sound is counteracted with eddy noise generated when the fan wheel rotates. Moreover, the method for decreasing eddy noise is also provided.

A turbomachine and method for operating a turbomachine comprising a first rotatable component and a second rotatable component each defining a rotatable speed mechanically independent of one another, and an electric machine electrically coupled to the first rotatable component and the second rotatable component such that a load level relative to the first rotatable component and the second rotatable component is adjustable is generally provided. The method includes adjusting a first load at a first rotor assembly of the electric machine electrically coupled to the first rotatable component such that a first speed of the first rotatable component is increased or decreased based on an engine condition and the first load; adjusting a second load at a second rotor assembly of the electric machine electrically coupled to the second rotatable component such that a second speed of the second rotatable component is decreased or increased based on the engine condition and the second load; and transferring electrical energy generated from at least one of the first rotatable component or the second rotatable component.

An air pump comprises a controller, a pump, a driving switch and a pressure sensor. The controller includes a central processing unit and defines an air inlet. The pump couples to the controller to inflate or discharge air from an inflatable body. The pump comprises a housing defining an inflating and a discharging port. The driving switch couples to the controller to implement switching between two or more air passage configurations. The pressure sensor couples to the central process unit to detect an internal pressure value of the inflatable body. The controller includes a wireless communication module which communicates with the central processing unit and a mobile terminal. The mobile terminal includes a terminal wireless communication module and a terminal input unit. The terminal wireless communication module communicates with the wireless communication module. The terminal input unit provides at least an inflation, a deflation, or a stop signal input.

An actuator operable to drive a thrust reverser in a gas turbine engine, wherein the thrust reverser comprises first and second translatable sleeves. The actuator comprises a first actuating member moveable so as to translate the first sleeve and a second actuating member moveable so as to translate the second sleeve. The actuator further comprises an interlock arrangement operable in a locked mode in which the first actuating member and second actuating member are locked so as to move together and in an unlocked mode in which at least one of the first actuating member and second actuator member is free to move independently of the other. Operation of the actuator to open or close the thrust reverser comprises a first mode wherein the interlock arrangement is in the locked mode and a second mode wherein the interlock arrangement is in the unlocked mode.

A control system for controlling the operation of a plurality of micro thrusters arranged in a plurality of parallel horizontal rows and a plurality of parallel vertical columns, the control system requires a power source, a first plurality of power lines connected to the power source and coupled to at least one micro thruster of the plurality of micro thrusters in a horizontal row of the plurality of parallel horizontal rows, a second plurality of power lines connected to the power source and coupled to at least one micro thruster of the plurality of micro thrusters in a vertical column of the plurality of parallel vertical columns, and a control unit coupled to the power source to control activation of the first plurality of power lines and activation of the second plurality of power lines.

A steam valve includes a valve body having a valve seat in a steam channel, a valve stem configured to close the steam channel by coming in contact with the valve seat and to open the steam channel by moving from the valve seat and a guide portion configured to slidably guide the valve stem in a moving direction thereof. The guide portion has a guide body that encloses the valve stem from a radial outer side of the valve stem and a guide bush that is detachably fixed inside the guide body, has an inner surface which abuts and slides on an outer circumferential surface of the valve stem, and is formed of a material having corrosion resistance.

An actuator system including a harmonic drive operable to drive a variable vane system of a gas turbine engine.

An actuator system including a harmonic drive operable to drive a variable vane system of a gas turbine engine.

A turbocharger assembly (1) comprises a turbine (4), a compressor (6), a housing (8), one or more electronic components (38, 40, 41, 42, 45, 47, 50, 51, 52, 54, 58) and a pettier device (46). The pettier device (46) is configured to provide electrical power to the one or more electronic components (38, 40, 41, 42, 45, 47, 50, 51, 52, 54, 58).