Ihi Corporation

Ihi Aerospace Co., Ltd.

Noriko Morioka

Hitoshi Oyori

Naoki Seki

Hiroyuki Kimura

Shinsuke Matsuno

Akihiko Oyama

Daiki Kakiuchi

Hiroyuki Asakura

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 heat exhaust system for an on-aircraft electric generator, includes: a fuel pump which is driven by electric power generated by an electric generator installed in an aircraft, and which measures and supplies fuel to an engine of the aircraft; a first heat exchanger which releases heat generated by the electric generator into the fuel supplied to the engine; a fuel flow rate determiner which determines a flow rate of the fuel supplied to the engine by the fuel pump; an electric generator output determiner which determines an output from the electric generator; and a heat release controller which controls heat release at the first heat exchanger by using at least one of the flow rate of the fuel determined by the fuel flow rate determiner and the output determined by the electric generator output determiner as a control parameter.

Heat exhaust system for on-aircraft electric generator

Two systems of a first pump unit and a third pump unit that supply fuel of a fuselage fuel tank, and a second pump unit and a fourth pump unit that supply fuel of fuel tanks in both right and left wings are provided corresponding to a left-wing engine and a right-wing engine, respectively. A supply source of the fuel to be supplied to the left-wing engine or the right-wing engine is switched by switching of the pump unit to be turned on.

Fuel supply apparatus for aircraft engine

A fuel supply device according to the present invention comprises a first fuel pump for forcing fuel from a fuel tank to a fuel passage, a first electric motor for driving the first fuel pump, a second fuel pump for forcing fuel from the fuel tank to the fuel passage, a second electric motor for driving the second fuel pump, a supply flow rate sensor for detecting flow rate in the supply passage, and a control device for controlling the flow rate in the supply passage to follow a desired value thereof, by regulating rotational speeds of the first and second electric motors depending on a difference between the desired value and a detected value of flow rate in the supply passage.

Fluid supply device

Heat exchangers are adjacent to electric driving units. Electric blowers of electric blower units rotate at rotational speed corresponding to amounts of heat generation of the electric driving units and suck air (ventilation air and outboard air). The sucked-in air passes through the heat exchangers that are adjacent to the electric driving units.

System for cooling electric driving unit of aircraft

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 electricity generation system according to the present invention comprises a first electric generator designed to generate electricity by rotation of a high-pressure shaft of a compressor constituting a jet engine, a second electric generator designed to generate electricity by rotation of a low-pressure shaft of the compressor, a power distributor for distributing power generated by the first and second electric generators among a multiple loads, a first power regulation device for regulating power output of the first electric generator, a second power regulation device for regulating power output of the second electric generator, and a power control device which manipulates the first and second power regulation devices to ensure a specified amount or greater of jet engine surge margin.

Growing community of inventors

Tokyo, Japan

Noriko Morioka