Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: An electric taxiing system of an aircraft includes: a wheel of an aircraft; a taxiing motor which is rotated together with the wheel in landing of the aircraft to apply breaking force to the wheel and to generate regenerative power according to the breaking force, and which rotates the wheel in taxiing of the aircraft; and a power supply control unit which supplies the regenerative power to an electric element of the aircraft, the electric element being driven in order for the aircraft to perform landing or re-takeoff after cancelling landing.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: There is provided an inexpensive rolling element used under high interface pressure such as induction hardened gears, the rolling element being improved in the seizure resistance of its tooth flanks and having a temper hardness of HRC 50 or more at 300° C. To this end, the rolling element is made from a steel material containing at least 0.45 to 1.5 wt % C and one or more alloy elements selected from 0.1 to 0.5 wt % V and 0.3 to 1.5 wt % Cr, and has a rolling contact surface layer having a structure tempered at low temperature in which 2 to 18% by volume cementite disperses in a martensite parent phase formed by induction heating and cooling and containing 0.25 to 0.8 wt % carbon solid-dissolving therein.

Abstract: There is provided an inexpensive rolling element used under high interface pressure such as induction hardened gears, the rolling element being improved in the seizure resistance of its tooth flanks and having a temper hardness of HRC 50 or more at 300° C. To this end, the rolling element is made from a steel material containing at least 0.45 to 1.5 wt % C and one or more alloy elements selected from 0.1 to 0.5 wt % V and 0.3 to 1.5 wt % Cr, and has a rolling contact surface layer having a structure tempered at low temperature in which 2 to 18% by volume cementite disperses in a martensite parent phase formed by induction heating and cooling and containing 0.25 to 0.8 wt % carbon solid-dissolving therein.

Abstract: There is provided an inexpensive rolling element used under high interface pressure such as induction hardened gears, the rolling element being improved in the seizure resistance of its tooth flanks and having a temper hardness of HRC 50 or more at 300° C. To this end, the rolling element is made from a steel material containing at least 0.45 to 1.5 wt % C and one or more alloy elements selected from 0.1 to 0.5 wt % V and 0.3 to 1.5 wt % Cr, and has a rolling contact surface layer having a structure tempered at low temperature in which 2 to 18% by volume cementite disperses in a martensite parent phase formed by induction heating and cooling and containing 0.25 to 0.8 wt % carbon solid-dissolving therein.

Abstract: The pitting resistance of a gear is increased by hardening its tooth flanks through application of carburizing/quenching, bright hardening and induction hardening to a steel material capable of providing significantly improved softening resistance in tempering at a low temperature of 300 to 350° C. To this end, the steel material prepared so as to satisfy the relationship described by: 5?4.3×Si (wt %)+7.3×Al (wt %)+3.1×V (wt %)+1.5×Mo (wt %)+1.2×Cr (wt %)×(0.45÷C (wt %)) is carburized such that the carbon concentration of its carburized surface layer is adjusted to 0.6 to 0.9 wt %; and the steel material is subjected to quenching and tempering at 300° C. or less subsequently to the carburization process, or alternatively the steel material is once cooled after the carburization process and then subjected to treatments of re-heating hardening and tempering at 300° C. or less so that a hardness of HRC 58 or more is ensured by the tempering process at 300° C.

Abstract: The pitting resistance of a gear is increased by hardening its tooth flanks through application of carburizing/quenching, bright hardening and induction hardening to a steel material capable of providing significantly improved softening resistance in tempering at a low temperature of 300 to 350° C. To this end, the steel material prepared so as to satisfy the relationship described by: 5?4.3×Si(wt %)+7.3×Al(wt %)+3.1×V(wt %)+1.5×Mo(wt %)+1.2×Cr(wt %)×(0.45÷C(wt %)) is carburized such that the carbon concentration of its carburized surface layer is adjusted to 0.6 to 0.9 wt %; and the steel material is subjected to quenching and tempering at 300° C. or less subsequently to the carburization process, or alternatively the steel material is once cooled after the carburization process and then subjected to treatments of re-heating hardening and tempering at 300° C. or less so that a hardness of HRC 58 or more is ensured by the tempering process at 300° C.