Ihi Corporation

Mitsubishi Denki Kabushiki Kaisha

Naoki Seki

Toshikazu Kobayashi

Fuminori Suzuki

Yasuhiko Yamamoto

Akihiro Shimamura

Hirotaka Sugawara

Noriko Morioka

Takashi Sato

Hiroyuki Kimura

Shinsuke Matsuno

Hitoshi Oyori

Kenji Takamiya

Masahiro Tanida

Yasunori Nihei

Akihiko Oyama

Seiko Ikeuchi

Shotaro Ishii

An energy recovery device for an aircraft includes: a turbine that is provided between a cabin of the aircraft and an opening for discharging cabin discharge air from the cabin to the outside of the aircraft and is operated by only the cabin discharge air; and a power generator that is driven by the turbine.

Energy recovery device for aircraft

A fuel supply system includes a gear pump, and a minimum pressurizing check valve including a cylinder and a piston that partitions the internal space of the cylinder into a first chamber that communicates with the metering section and a second chamber that communicates with a system inlet, the piston is spring-biased in a direction toward the first chamber, a side wall of the cylinder is provided with an outflow port having an opening degree adjusted as the piston moves back and forth, the minimum pressurizing check valve keeps a differential pressure between the system inlet and the outlet of the metering section constant when the rotation speed of the gear pump is equal to or more than a lower threshold and is equal to or less than an intermediate threshold.

Fuel supply system and fuel supply method for aircraft gas turbine engine

Provided is a stator including a coil of a winding of a flat wire conductor, a stator core including a slot for housing a part of the coil, and a flow passage part through which a coolant flows, provided between a wall part of the slot and an outer surface of the coil facing the wall part. The extension shape of the flow passage part from an inlet to an outlet for the coolant changes along the axial direction of the stator core. The flow passage part is, for example, a concave part formed on the wall part of the slot.

Electric motor stator and electric motor

A rotor of an electrical rotating device includes a rotor core, plural permanent magnets mounted on an outer circumference of the rotor core, a retaining sleeve that holds the permanent magnets from their outer side, a cooling fluid flow channel formed on each surface of the permanent magnets on a side of the retaining sleeve [or on each surface on a side of the rotor core], and a seal ring. The retaining sleeve is configured of plural divided sleeves divided along a direction of a rotation axis of the rotor. A seam is formed between adjacent divided sleeves in the plural divided sleeves. The seal ring covers the seam from an outer circumferential side [or an inner circumferential side].

Rotor with cooling fluid flow channels formed in permanent magnets

An aircraft air conditioning device provided in an aircraft includes: a plurality of base units each of which is provided with two electric compressors connected in series to an air flow path; a temperature controller which is configured to adjust a temperature of air discharged from a compressor of the two electric compressors; and a control device which is configured to control the plurality of base units and the temperature controller and each of the plurality of base units is configured to supply compressed air discharged from the temperature controller to an air-conditioned space as conditioned air.

Aircraft air conditioning device

An electric generator equipped in a multi-shaft gas turbine engine for aircraft, includes: a rotor attached to the rear end portion of a low-pressure shaft rotatably supported by a bearing in the gas turbine engine; a stator provided around the rotor; wherein the electric generator has no structure to support the low-pressure shaft and the rotor.

Electric generator and multi-shaft gas turbine engine for aircraft equipped with electric generator

A fuel supply control device () is configured to generate an operation amount used for feedback-controlling rotation of a gear pump () based on a deviation of a detected fuel flow rate with respect to a target flow rate, wherein the fuel supply control device generates the operation amount such that a rotation speed of the gear pump is equal to or greater than a predetermined lower limit rotation speed Nmin so as to protect a bearing of the gear pump.

Fuel supply control device

A system capable of appropriately cooling a generator and a power cable connected to the generator, disposed in a hot section of a turbo-fan engine, regardless of a rating of the engine is provided. The system includes: a junction box; a bypass air duct that supplies, to the junction box, air extracted from a portion of a bypass flow path of the engine on a side further downstream than a fan outlet; a core air duct that supplies, to the junction box, air extracted from a portion of a core flow path of the engine on a side further upstream than a compressor outlet; and a cooling air duct that extends from the junction box to a space for accommodating the generator, and valves capable of being independently controlled to open and close are provided at downstream ends of the bypass air duct and the core air duct.

Generator cooling system for turbo-fan engine

In an external gear pump, a first bushing of a rotational shaft of a first gear has a second surface facing to a first surface of a pump body. A recess for supplying high-pressure lubricating oil between an inner circumferential surface of the first bushing and an outer circumferential surface of the rotational shaft is opened on the inner circumferential surface within a low pressure range associating with an inlet chamber of fluid. A bushing-side supply passage for supplying the high-pressure lubricating oil to the recess is formed within the first bushing. A bushing-side inlet port of the bushing-side supply passage is opened on the second surface within a high pressure range associating with an outlet chamber of the fluid. A body-side supply passage for supplying the high-pressure lubricating oil to a body-side supply port opened on the first surface is formed within the pump body.

External gear pump

A cooling system includes: a core casing configured to house a compressor, a combustion chamber, and a turbine; a tail cone configured to form at least part of an exhaust passage of the turbine together with the core casing; struts configured to connect the core casing with a support body of the tail cone; a housing installed in the tail cone, configured to house an electrical apparatus; and at least one primary duct configured to connect between an internal space of the housing and an outlet passage of the compressor or a discharge port of a blower installed in a gas turbine engine via at least one of the struts and a radial outside of the core casing.

Cooling system for aircraft gas turbine engine

A fuel supply control device is provided in which a parallel flow path of an orifice and a pressurizing valve is used as a complex pressurizing valve for a fuel supply amount, and which controls a fuel supply pump on the basis of a pressure difference before and after the complex pressurizing valve that has been detected by a pressure difference meter. When the rotational speed of the fuel supply pump is below a predetermined threshold value, the fuel supply pump is controlled on the basis of a first fuel measurement amount, and the fuel supply pump is controlled on the basis of a second fuel measurement amount.

A fuel supply control device controls a fuel supply pump based on a front-rear differential pressure across a metering valve for a fuel supply amount, which is detected by a differential pressure gauge, using parallel flow passages of an orifice and a pressurizing valve as the metering valve, in which the fuel supply control device includes a first control amount generation unit generating a first control amount based on the front-rear differential pressure, a second control amount generation unit generating a second control amount based on the rotation speed of the fuel supply pump, a control amount selection unit, a subtractor, and a control calculation unit, in which the control amount selection unit selects the first control amount in a case where the rotation speed is equal to or lower than a predetermined threshold and select the second control amount in a case where the rotation speed exceeds the threshold.

Provided is a turbo fan engine (TF) provided with a power transmission device that switches main shafts (MSs) connected to a starter generator (SG) so as to perform power transmission, between at startup and after the startup. The TF includes a first MS and a second MS. The power transmission device includes a first shaft, an intermediate shaft, and a second shaft that are coaxially disposed, and a clutch. The first shaft is connected to the first MS through bevel gears, the intermediate shaft is disposed outside of the first shaft and is connected to the SG through bevel gears, and the second shaft is disposed outside of the intermediate shaft and is connected to the second MS through bevel gears. When, out of any two adjacent shafts of the first shaft, the intermediate shaft, and the second shaft, an inner shaft tries to rotate at a speed higher than a speed of an outer shaft, the clutch causes the both shafts to engage with each other and to rotate at the same speed, and transmits power, whereas when the outer shaft tries to rotate at a speed higher than a speed of the inner shaft, the clutch causes the both shafts to disengage from each other, and does not transmit power.

Turbo fan engine

A cooling device applicable to an airplane having a pressurized cabin and a ram air channel for cooling an electronic device arranged in the pressurized cabin, is comprised of a partition wall separating the pressurized cabin from the ram air channel; and a heat exchanger thermally in contact with the electronic device and exposed to the ram air channel so as to radiate heat to a ram air.

Cooling apparatus for cooling electronic device in aircraft

An inter-zone connection communication method for carrying out a general connection communication and an inter-zone connection communication at the same time, using general connection channels which are used for general connection communication between connection stations in a radio communication area of one relay station, and using inter-zone connection channels which are used for inter-zone connection communication between a connection station in a radio communication area of one relay station and another connection station in another relay station, comprising a step of carrying out line control by changing an assignment ratio of the general connection channels to the inter-zone connection channels according to respective traffic quantities of the general connection communication and the inter-zone connection communication. Thereby, traffic processing capability of the system can be improved.

Growing community of inventors

Tokyo, Japan

Naoki Seki