Systems and methods axe disclosed herein that generally involve a double pinch criterion for optimization of regenerative Rankine cycles. In some embodiments, operating variables such as bleed extraction pressure and bleed flow rate are selected such that a double pinch is obtained in a feedwater heater, thereby improving the efficiency of the Rankine cycle. In particular, a first pinch point is obtained at the onset of condensation of the bleed and a second pinch point is obtained at the exit of the bleed from the feedwater heater. The minimal approach temperature at the first pinch point can be approximately equal to the minimal approach temperature at the second pinch point. Systems that employ regenerative Rankine cycles, methods of operating such systems, and methods of optimizing the operation of such systems are disclosed herein in connection with the double pinch criterion.

The present disclosure is directed to a variable area turbine nozzle. The variable area turbine nozzle includes a first vane segment, a second vane segment arranged with the first vane segment, and a trailing edge segment arranged with the first and second vane segments. The vane also includes a first actuating system for pivoting the second vane segment with respect to the first vane segment and a second actuating system for pivoting the trailing edge with respect to the first and second vane segments.

A multi-redundancy electromechanical servo system for regulating a liquid rocket engine, comprising a triple-redundancy servo controller (1), a double-redundancy servo driver (2), double-winding electromechanical actuators (4, 5), a triple-redundancy position sensor (6), a thrust regulator (8) and a mixed ratio regulator (9). Engine thrust, a mixed ratio regulation instruction and a feedback signal of the triple-redundancy position sensor are inputted to the triple-redundancy servo controller, and the triple-redundancy servo controller outputs thrust and mixed ratio regulation PWM wave control signals to the double-redundancy servo driver. The double-redundancy servo driver outputs a three-phase variable-frequency variable-amplitude sine wave current to drive the double-winding electromechanical actuators to drive the thrust regulator and the mixed ratio regulator to move, thus achieving engine thrust and mixed ratio regulation. The present servo system has a simple system and excellent control characteristics, has the ability to “control a two-degree fault operation and drive a one-degree fault operation”, and significantly improves the reliability and usage maintainability of the thrust and mixed ratio regulation of the liquid rocket engine. Also disclosed is a method for implementing the foregoing multi-redundancy electromechanical servo system.

A rotor for a gas turbine engine has: a first rotor disk; an interstage flange that extends from the first rotor disk to a flange end portion that has an axial end surface and first radial outer and inner surfaces; a circumferential groove, formed in the flange end portion and extending from the axial end surface toward the first rotor disk; radial outer and inner slots formed in the first radial outer and inner surfaces along the circumferential groove and extend through the first radial outer and inner surfaces; and a valve member disposed within the circumferential groove and is secured within the circumferential groove when the flange end portion is connected to a second rotor disk, wherein the valve member deflects from rotor rotational speeds to seal or unseal the radial outer slot.

An apparatus for a thrust reverser actuation system (“TRAS”), the apparatus comprising: an input shaft; a first component located concentrically around the input shaft; a second component located concentrically around the first component; a first balls crew mechanism between the input shaft and the first component, and configured such that rotational movement of the input shaft causes a translational movement of the first component via the first ballscrew mechanism; and a second ballscrew mechanism between the first component and the second component, and configured such that rotational movement of the first component causes a translational movement of the second component via the second ballscrew mechanism.

An electric power generation controller for use in an aircraft to control an electric power generating apparatus including a manual transmission which changes speed of rotational power of an aircraft engine, transmits the rotational power to an electric power generator, and includes a plurality of gear stages. The electric power generation controller includes: a rotational frequency receiving section configured to receive an input rotational frequency or an output rotational frequency of the manual transmission as a monitoring rotational frequency; and a manual transmission control section configured to, when the monitoring rotational frequency exceeds a first threshold, output a shift-down signal to perform shift-down from an upper stage to a lower stage, and when the monitoring rotational frequency falls below a second threshold, output a shift-up signal to perform shift-up from the lower stage to the upper stage, the first threshold being set to a value larger than the second threshold.

A bleed valve for use in a gas turbine engine of an aircraft includes a high-pressure cavity coupled to a valve terminal, which is itself coupled to a cap, which cap includes a valve seat configured to be sealed by a tube that serves as the valve gate. The tube is operably coupled to a movable end of a bellows, which is positioned within the high-pressure cavity. The opening and closing of the valve is controlled by the movement of the bellows within the high-pressure cavity, and, in turn, the movement of the tube towards the valve seat, with the valve closing as the bellows compresses.

An aspect of the present disclosure provides a diagnosis device for an internal combustion engine. The internal combustion engine 1 includes a variable geometry type turbocharger 14, and the turbocharger includes a variable vane 28, a link mechanism configured to operate the variable vane, and an actuator 29 configured to drive the link mechanism. The diagnosis device includes a control unit 100 configured to control an opening degree of the variable vane by controlling the actuator. The control unit determines that an abnormality has occurred in the link mechanism of the turbocharger when an operating time of the internal combustion engine in a predetermined operating region exceeds a predetermined upper limit value and a differential pressure between a target boost pressure determined according to an operating state of the internal combustion engine and an actual boost pressure exceeds a predetermined upper limit value.

An actuator for a thrust reverser includes a ball screw, a ball nut coupled to the ball screw, and a gerotor coupled to the ball screw. The gerotor includes an inner rotor coupled to the ball screw and an outer rotor. The outer rotor includes a plurality of bores. The actuator includes a lock system coupled to the outer rotor. The lock system is to enable the gerotor to rotate the ball screw in an unlocked state and to inhibit a rotation of the ball screw in a lock state. The lock system includes a piston coupled to a piston housing and a grippable member coupled to the piston housing. The piston is received in one of the bores in the lock state, and the grippable member is to move the piston housing relative to the gerotor to move the lock system to the unlocked state.

The subject matter of this specification can be embodied in, among other things, a thrust reverser tertiary lock apparatus that includes a probe affixed to an aircraft engine frame and having a shaft having a barb at a first end and configurable to a first configuration and a second configuration, and a receiver affixed to a thrust reverser transcowl slider configured to accommodate the barb and having an end wall with an aperture defined therein, the aperture shaped to permit escapement of the barb in the first configuration and prevent escapement of the barb in the second configuration.