Abstract: Provided is a toroidal continuously variable transmission that can create a jet of oil resistant to the influence of wind generated by rotation of a power roller, thereby feeding a sufficient amount of oil to the power roller to cool the power roller with the oil; and a drive mechanism-integrated electricity generation apparatus for an aircraft, the electricity generation apparatus including the toroidal continuously variable transmission. The toroidal continuously variable transmission includes a discharge structure including an outlet that discharges an oil. The discharge structure includes first and second oil passages connected with each other inside the discharge structure, and arranged such that the oil flowing through the first oil passage and the second oil passage collide with each other in the vicinity of the outlet and that a jet of oil discharged from the outlet forms a flattened shape extending along a rotational direction of the power roller.

Abstract: A transmission structure of a helicopter according to one aspect is a transmission structure that transmits power from a prime mover to a rotary wing in the helicopter. The transmission structure includes: a housing; an input shaft that transmits the power of the prime mover to a gear arranged in the housing; a bearing supporting the input shaft in the housing such that the input shaft is rotatable, the bearing including an annular inner ring that holds the input shaft, an annular outer ring that is arranged outside the inner ring in a radial direction and fixed to the housing, and rolling elements sandwiched between the inner ring and the outer ring; and a sleeve that is sandwiched between an inner peripheral surface of the inner ring and the input shaft and is lower in heat conductivity than the inner ring and the input shaft.

Abstract: A toroidal continuously variable transmission including a power roller; a support supporting the power roller rotatably; a thrust bearing receiving a load of the power roller in a direction along a rotating axis; and an oil passage supplying lubricating oil to the thrust bearing. A surface of the power roller opposing the support includes a first bearing grooved and the support opposing the power roller includes a second bearing groove. A virtual axis of a discharge port in the oil passage reaches a bearing groove that is one of the first bearing groove and the second bearing groove. Viewed from a direction perpendicular to the rotation axis, a portion of a retainer located at a radially inner side of a retaining hole of the retainer and a portion located at a radially inner side of the bearing groove are located at sides opposite to each other across the virtual axis.

Abstract: A gas turbine engine including: an exhaust diffuser including an inner tube and an outer tube that form therebetween an annular exhaust passage; a bearing chamber formed radially inside the inner tube for accommodating a bearing that supports a rotor of a turbine; a plurality of hollow struts extending across the exhaust passage; an oil introduction passage extending through one of the struts for introducing oil to be supplied to the bearing chamber; an oil drain passage extending through one of the struts for draining the oil from an exhaust oil inlet opened on a bottom surface of the bearing chamber; and an oil discharge passage for discharging a portion of the oil having passed through the oil introduction passage toward the oil drain inlet.

Abstract: Provided is a toroidal continuously variable transmission that can create a jet of oil resistant to the influence of wind generated by rotation of a power roller, thereby feeding a sufficient amount of oil to the power roller to cool the power roller with the oil; and a drive mechanism-integrated electricity generation apparatus for an aircraft, the electricity generation apparatus including the toroidal continuously variable transmission. The toroidal continuously variable transmission includes a discharge structure including an outlet that discharges an oil. The discharge structure includes first and second oil passages connected with each other inside the discharge structure, and arranged such that the oil flowing through the first oil passage and the second oil passage collide with each other in the vicinity of the outlet and that a jet of oil discharged from the outlet forms a flattened shape extending along a rotational direction of the power roller.

Abstract: A transmission cooling assembly of a helicopter includes: a transmission including a speed change structure that changes the speed of rotation produced by rotational power input from a prime mover and outputs the resulting rotational power and a housing accommodating the speed change structure; a cowl covering at least a part of an outer surface of the housing, with a gap defined between the cowl and the outer surface; and a flow structure that allows external air to flow through the gap.

Abstract: A transmission lubricating assembly of a helicopter includes: a transmission including a speed change structure that changes the speed of rotation produced by rotational power input from a prime mover and outputs the resulting rotational power and a housing accommodating the speed change structure; and a lubricator that lubricates the speed change structure. The lubricator includes a collector that collects a mist of a lubricating oil in an internal space of the housing and a dropper that is disposed below the collector and that applies droplets of the lubricating oil to the speed change structure, the droplets resulting from the collected mist being gathered under its own weight.

Abstract: Provided is a toroidal continuously variable transmission that can achieve suitable oil feed both for lubrication at contact interfaces between a power roller and discs and for cooling of the power roller; and a drive mechanism-integrated electricity generation apparatus for an aircraft, the electricity generation apparatus including the toroidal continuously variable transmission. The toroidal continuously variable transmission includes at least one lubrication outlet that discharges an oil toward at least one contact interface between an input or output disc and the power roller; and at least one cooling outlet that discharges the oil toward the power roller. The cooling outlet and the lubrication outlet are arranged such that a distance between the cooling outlet and a point at which the oil discharged from the cooling outlet contacts the power roller is smaller than a distance between the lubrication outlet and the contact interface.

Abstract: A gear cooling structure includes: a gear including a plurality of teeth extending in a particular direction; and a nozzle that jets out oil toward a toothed surface of the gear. The nozzle extends in the particular direction, and has a width that is narrower than a gap between tips of the plurality of teeth.

Abstract: A gas turbine engine including: an exhaust diffuser including an inner tube and an outer tube that form therebetween an annular exhaust passage; a bearing chamber formed radially inside the inner tube for accommodating a bearing that supports a rotor of a turbine; a plurality of hollow struts extending across the exhaust passage; an oil introduction passage extending through one of the struts for introducing oil to be supplied to the bearing chamber; an oil drain passage extending through one of the struts for draining the oil from an exhaust oil inlet opened on a bottom surface of the bearing chamber; and an oil discharge passage for discharging a portion of the oil having passed through the oil introduction passage toward the oil drain inlet.

Abstract: A gear cooling structure includes: a gear including a plurality of teeth extending in a particular direction; and a nozzle that jets out oil toward a toothed surface of the gear. The nozzle extends in the particular direction, and has a width that is narrower than a gap between tips of the plurality of teeth.

Abstract: A gas turbine engine and a turbine stator assembly which is capable of being cooled effectively with a small amount of air. The stator assembly comprises a stator vane disposed to be exposed to a combustion gas passage. The stator vane comprises a cooling passage defined therein. The cooling passage is disposed on an upstream of the gas turbine engine and extending in a radial direction with respect to a central axis of the gas turbine engine. The stator vane also has an inlet communicated to a radially outward end of the cooling passage. The stator vane further has an adjustment member secured to the stator vane so that it covers the inlet. The adjustment member has two apertures for guiding a cooling air radially inwardly through the inlet into the cooling passage. The two apertures are spaced away from each other along a camber line of the stator vane.

Abstract: A gas turbine engine and a turbine stator assembly which is capable of being cooled effectively with a small amount of air. The stator assembly comprises a stator vane disposed to be exposed to a combustion gas passage. The stator vane comprises a cooling passage defined therein. The cooling passage is disposed on an upstream of the gas turbine engine and extending in a radial direction with respect to a central axis of the gas turbine engine. The stator vane also has an inlet communicated to a radially outward end of the cooling passage. The stator vane further has an adjustment member secured to the stator vane so that it covers the inlet. The adjustment member has two apertures for guiding a cooling air radially inwardly through the inlet into the cooling passage. The two apertures are spaced away from each other along a camber line of the stator vane.

Abstract: A trigger circuit comprises a shaping circuit connected between an input terminal receiving a trigger signal and an avalanche transistor. The shaping circuit has a pass band whose upper limit frequency is much lower than the frequency component of the leading edge of the input trigger signal, and it has a saturation characteristic to provide a pulse whose time width is sufficient to start the avalanche transistor.