A system and a method for the automatic starting of the engines of a twin-engine aircraft. When a first engine is made by the pilots of the aircraft to follow an automatic starting procedure, this engine follows the conventional four-phase starting cycle. The rotor of the high-pressure stage of the second engine is spun up for a predetermined duration and to a speed that is substantially constant and less than the nominal value during the starting cycle for the first engine. Once the starting cycle for the first engine is complete, the second engine is made by the pilots of the aircraft to follow an automatic starting procedure. The starting cycle for the second engine comprises just three phases.

A turbine airfoil for a gas turbine engine includes a pressure sidewall extending along a spanwise direction, and from a leading edge of the airfoil towards the trailing edge of the airfoil. The turbine airfoil additionally includes a suction sidewall also extending along the spanwise direction, and from the leading edge towards the trailing edge. The pressure sidewall and suction sidewall define a cooling air cavity therebetween, and one or both of the pressure sidewall and suction sidewall define a trailing edge cooling channel extending from the cooling air cavity substantially to the trailing edge. Additionally, one or both of the pressure sidewall and suction sidewall include a plurality of pressure drop members extending partially into the trailing edge cooling channel for reducing an amount of cooling air flowing therethrough from the cooling air cavity.

A gas turbine engine includes a fan and an engine core configured to provide rotational power during operation of the gas turbine engine. The engine core includes a compressor, a combustor, and a turbine. An oil sump is located in the engine core and is configured to collect oil from the engine core. The gas turbine engine further includes a gearbox configured to be driven by the engine core during operation of the gas turbine engine and an oil pump assembly configured to move the oil from the oil sump to an oil tank and/or to the engine core.

A method, system, and apparatus for the thermal storage of energy generated by multiple nuclear reactor systems including diverting a first selected portion of energy from a portion of a first nuclear reactor system of a plurality of nuclear reactor systems to at least one auxiliary thermal reservoir, diverting at least one additional selected portion of energy from a portion of at least one additional nuclear reactor system of the plurality of nuclear reactor systems to the at least one auxiliary thermal reservoir, and supplying at least a portion of thermal energy from the auxiliary thermal reservoir to an energy conversion system of a nuclear reactor of the plurality of nuclear reactors.

In various embodiments, a thrust reverser system may comprise a first cascade, a second cascade, an actuator, and a structural connecting member. The actuator may be radially disposed between the first cascade and the second cascade. The structural connecting member may be adjacent the actuator. The structural connecting member may be configured to structurally join the first cascade and the second cascade.

A solar power generating system for generating electricity and providing heat includes; at least one generator for generating the electricity; a heating element for heating a heat transfer fluid; a turbocharger having at least one turbocharger turbine and at least one turbocharger compressor, wherein the at least one turbocharger compressor is adapted to receive and pressurize the heat transfer fluid, and the at least one turbocharger turbine is coupled to the at least one turbocharger compressor, wherein the at least one turbocharger compressor receiving and expanding a heated compressed heat transfer fluid coming from the heating element to drive the at least one turbocharger compressor and; a control unit configured to control the solar power generating system by comparing thermophysical properties obtained from more than one sensors placed in the solar power generating system with predetermined data in the control unit.

A masking system for a turbine including a first quantity of blades attached to a rotor and arranged adjacent one another to define a blade row with each blade including a blade root, includes a second quantity of center plates. Each center plate is disposed between two adjacent blades and includes a resilient member in contact with each of the two adjacent blades, and a first attachment member operable to attach the center plate to the rotor. The system includes a third quantity of side covers, each side cover positioned adjacent the blade root of one of the blades and connected to one of the center plates, each side cover including a resilient member positioned to surround a portion of the adjacent blade root, and a second attachment member operable to attach the side cover to the rotor.

Gas turbine engine compressor bleed assembly includes annular bleed plenum between annular outer and inner casings circumscribing compressor flowpath of compressor, upstream and downstream bleed ports disposed through inner casing and between compressor flowpath and plenum at upstream and downstream stages. Bleed path extends from downstream bleed port through bleed plenum and out bleed outlet disposed through outer casing. Autonomously actuated valve such as poppet valve disposed in bleed path or downstream bleed port. Autonomously actuated or poppet valve may be set to open at take-off and/or climb. Bleed outlet may be customer and domestic or engine bleed outlet disposed through outer casing and in fluid bleed air communication with bleed plenum. Another assembly may include annular forward and aft bleed outlets connected to plenums. Bleed path extends from downstream bleed port through plenums and out forward bleed outlet.

A turbomachine for a vehicle is provided. The turbomachine includes a manifold configured to channel a flow of fluid therethrough; a first pressure measurement device in communication with the manifold and configured to determine a first pressure difference; a second pressure measurement device in communication with the manifold and configured to determine a second pressure difference; a data selector device in communication with the first pressure measurement device and the second pressure measurement device, wherein the data selector device receives the first and second pressure difference and uses a logic circuit to generate a single pressure signal; and an engine controller operably coupled to the data selector device such that the engine controller receives the single pressure signal indicating a pressure differential of the manifold.

A compressed-air-storing power generation apparatus 1 comprises a plurality of compression/expansion devices 14 having a function of producing compressed air using electric power and a function of generating electricity using compressed air, an accumulator 10 that is fluidly connected to the plurality of compression/expansion devices 14 and that accumulates compressed air, and a control apparatus 16 that stops first compression/expansion devices 14 which are being driven and drives second compression/expansion devices 14 which have stopped when a charge/discharge command value to switch between charging and discharging is generated.