Kawasaki Jukogyo Kabushiki Kaisha

Other

Tatsuhiko Goi

Kenichiro Tanaka

Hideyuki Imai

Hidenori Arisawa

Koji Watanabe

Isao Fujii

Kenichi Nakashima

Motohiko Nishimura

Hiroyasu Nishikawa

Kazushige Sugimoto

Akihito Abe

Katsuhiko Ishida

Tetsuya Matsuoka

Naoya Sekoguchi

Hiroaki Takami

Hiroshi Sakamoto

Kenta Umezaki

Kippei Matsuda

Masahide Kazari

Hirofumi Akahori

Koji Kawakami

Masaaki Higashi

Maiko Sato

Tooru Nishida

Masahide Nakamura

Shogo Fuchiwaki

Hiroyuki Ito

Hisashi Machida

Shinji Miyata

Kazuhiro Sato

Kenji Komatsu

Yukinobu Kohno

Yukinobu Kouno

Kenji Usuki

Yasutaka Hirota

Satoshi Otsuki

Masaaki Uenishi

Takayuki Isano

A compressed air supply system that extracts compressed air from a gas turbine engine and supplies the compressed air to an air conditioning pack of an airframe. The compressed air supply system includes: a low-pressure bleed air port that extracts compressed air from an upstream side of a high-pressure compressor; a high-pressure bleed air port that extracts compressed air from a downstream side of a front-stage portion of the high-pressure compressor; a main pipe extending from the low-pressure bleed air port toward the air conditioning pack; an auxiliary compressor that is located at the main pipe and increases pressure of the compressed air; a high-pressure bleed air pipe that couples the main pipe to the high-pressure bleed air port; a high-pressure bleed air valve located at the high-pressure bleed air pipe; and circuitry that opens the high-pressure bleed air valve when the circuitry determines that an insufficient pressure state occurs.

Compressed air supply system

A compressed air supply system includes: a bleed air passage; an auxiliary compressor structure including a compressor inlet and a compressor outlet, the compressor inlet being fluidly connected to the bleed air passage; a supply passage which is fluidly connected to the compressor outlet and through which compressed air from the auxiliary compressor structure is supplied to an air cycle machine; an accessory gear box; and a continuously variable transmission structure that changes speed of rotational driving force output from the accessory gear box and rotates the auxiliary compressor structure. The continuously variable transmission structure and the auxiliary compressor structure are fixed to the accessory gear box, and the accessory gear box is fixed to the gas turbine engine.

A core engine including a core casing covering a low-pressure rotary structure and a high-pressure rotary structure and includes a passage of air flowing through the low-pressure and the high-pressure rotary structures; a fan located in front of the core engine; an inner cowl serving as an inner peripheral surface of a bypass passage that extends through the fan and bypasses the core engine; an accessory gear box that extracts power from the low-pressure or the high-pressure rotary structure and supplies the power to accessories; an auxiliary compressor attached to the accessory gear box, is driven by power of the accessory gear box, and increases pressure of compressed air extracted from the core engine; and a compressed air pipe that extends through an inside of a strut connecting the core engine and an airframe and supplies the compressed air having an increased pressure by the auxiliary compressor to the airframe.

Gas turbine engine for use in aircraft

An electric power generating apparatus for use in an aircraft is an electric power generating apparatus connected through an emergency cut-off device to a gear box such that the gear box can transmit power to the electric power generating apparatus, the gear box being configured to decrease speed of rotational power of an aircraft engine. The electric power generating apparatus includes: a manual transmission configured to change the speed of the rotational power transmitted from the emergency cut-off device and including a plurality of gear stages; and an electric power generator to which the rotational power which has been changed in speed by the manual transmission is transmitted.

Electric power generating apparatus for use in aircraft

An aircraft engine apparatus () includes: a rotating shaft (); a fan () driven by the rotating shaft; a fan case surrounding the fan; aircraft equipment () disposed upstream of the fan and, in a radial direction of the rotating shaft, disposed inward of a peripheral edge of the fan case; a casing () that accommodates at least part of the rotating shaft and supports the fan case; a first motive force transmitter () coupled to the rotating shaft and the fan; a second motive force transmitter () disposed inward of the first motive force transmitter in the radial direction of the rotating shaft and coupled to the rotating shaft and the aircraft equipment; and a support member () disposed between the first motive force transmitter and the second motive force transmitter, the support member coupling the casing and the aircraft equipment and supporting the aircraft equipment.

Aircraft engine power generator disposed inside of a stationary nose cone

An electric power generating device for an aircraft, which is driven by an output of an aircraft engine, comprises an input shaft to which a driving force of the engine is transmitted; a transmission arranged with the input shaft; an electric power generator arranged with the input shaft and the transmission and driven by an output of the transmission; a driving force transmission mechanism disposed on a first end side of the input shaft in an axial direction thereof, the driving force transmission mechanism being configured to transmit the output from the transmission to the electric power generator; and a casing including a mounting section on the first end side of the input shaft in the axial direction, wherein the transmission includes an input section provided on a second end side of the input shaft in the axial direction, the input section being configured to receive as an input a rotational driving force from the input shaft, and an output section provided on the first end side of the input shaft in the axial direction, the output section being configured to output to the driving force transmission mechanism the rotational driving force whose speed has been changed, and wherein the driving force transmission mechanism has an inner space and the input shaft is inserted into the inner space.

Electric power generating device for aircraft

A power generation system includes a continuously variable transmission, a power generator, a transmission driving device, an output-side speed detector, and electric power load device, and a controller. The electric power load calculation device detects current values and current values of respective phases of three-phase alternating current generated by the power generator, calculates electric power load of the power generator based on the detected values, and executes filtering by attenuating a higher harmonic of a set frequency when calculating the electric power load of the power generator. The controller executes feedback control of calculating and outputting a gear change command to the transmission driving device so an output-side rotational speed detected by the output-side speed detector becomes equal to an output-side target rotational speed corresponding to the set frequency. The controller also executes feedforward compensation of correcting the gear change command, based on the calculated electric power load.

Power generation system and method of controlling same

A power-on/off command is output to a breaker for switching when a frequency difference between a plurality of electric power supply sources is within a predetermined range and a phase difference between the plurality of electric power supply sources is within a predetermined range, in switching of electric power supply between the plurality of electric power supply sources. A generator drive rotation speed of a transmission device is feedback controlled so that the frequency difference is maintained at a value within the predetermined range and the phase difference is maintained at a value within the predetermined range when the detected frequency difference is within the predetermined range and the detected phase difference is within the predetermined range. A generator rotation speed command is calculated by adding to the rotation speed command of the transmission device an output value obtained by subjecting the detected phase difference to a proportional-integral-control.

Synchronous power-on/off control method and synchronous power-on/off controller

In a transmission device, a power roller transmits a rotational driving force from an input disc to an output disc in a transmission ratio (transmission gear ratio) corresponding to a tilt motion angle. The power roller allows the transmission ratio to be changed in such a manner that the position of the trunnion on which the power roller is tiltably supported is changed by a trunnion drive mechanism. Hydraulic oil is supplied from a hydraulic pump to the trunnion drive mechanism via a direction selector valve. The direction selector valve selects a flow direction of the hydraulic oil to supply the hydraulic oil to a speed reduction chamber or a speed increase chamber of the trunnion drive mechanism, and discharge the hydraulic oil from the other. In a case where a discharge condition is met, the controller controls a movement of the discharge valve to discharge the hydraulic oil from the speed increase chamber.

Transmission device and power generation system including transmission device

In a toroidal continuously variable transmission including at least one transmission unit including: an input disc and an output disc disposed coaxially; and a power roller tiltably interposed between the input disc and the output disc and configured to transmit a driving force from the input disc to the output disc, an integrally rotating member disposed so as to be spaced apart in an axial direction from at least one disc of the input disc and the output disc of each transmission unit and configured to rotate together with the at least one disc, and an annular interposed member provided between the at least one disc and the integrally rotating member and configured to rotate together with the at least one disc, are provided, and the interposed member is formed with a balance adjustment portion capable of adjusting weight balance in a circumferential direction.

Toroidal continuously variable transmission

An aircraft engine apparatus () includes: a rotating shaft (); a fan () driven by the rotating shaft; a fan case surrounding the fan from outside in a radial direction of the rotating shaft; a nose cone () disposed upstream of the fan; a casing () that accommodates at least part of the rotating shaft and supports the fan case; a first motive force transmitter () that transmits motive force of the rotating shaft to the fan; and a support member () disposed inward of the first motive force transmitter in the radial direction, the support member coupling the nose cone to the casing such that the support member supports the nose cone in a stationary state.

Aircraft engine apparatus

A transmission controller comprises an actuator which changes a roller position of a toroidal CVT to adjust the tilt motion angle of a power roller; a tilt motion angle information generation unit which generates information of the tilt motion angle; a position estimation unit which derives an estimated value of the roller position; and a position control unit which derives an operation command value of the actuator so that a deviation between a command value of the roller position and the estimated value of the roller position is cancelled. The position estimation unit is configured to derive the estimated value based on the information of the tilt motion angle which is generated by the tilt motion angle information generation unit, and the operation command value, and to compensate the estimated value based on an environment parameter which affects an operation of the power roller.

Transmission controller

A controller of a toroidal continuously variable transmission comprises a position control unit which outputs a driving signal to a hydraulic actuator to control a roller position. The hydraulic actuator includes a biasing mechanism which forcibly keeps the roller position at a predetermined position in a case where the driving signal meets a predetermined condition. The position control unit is configured to perform a start-up control during start-up of the toroidal continuously variable transmission. During the start-up control, the position control unit is configured to output the driving signal to reciprocate a spool of the hydraulic actuator in a case where a temperature of hydraulic oil supplied to the hydraulic actuator is lower than a reference temperature, and output the driving signal which meets the predetermined condition in a case where the temperature of the hydraulic oil has become equal to or higher than the reference temperature thereafter.

Controller of toroidal continuously variable transmission

A toroidal-type stepless transmission includes: at least a pair of an input disc and an output disc; a power roller tiltably provided between the pair of the input disc and the output disc, the power roller being configured to transmit a driving force from the input disc to the output disc; and disc shrouds covering the input disc and the output disc, respectively. Each of the disc shrouds has an outer peripheral portion formed with an oil discharge groove configured to discharge an oil within each disc shroud to the outside, the oil discharge groove penetrating from an inner surface of the disc shroud to an outer surface of the disc shroud and extending in a circumferential direction of the disc shroud.

Toroidal-type stepless transmission

In a continuously variable transmission including: a first transmission unit including a first input disc and a first output disc disposed coaxially and a power roller tiltably interposed between these discs; and a second transmission unit disposed coaxially with the first transmission unit, including a second input disc and a second output disc disposed coaxially and a second power roller tiltably interposed between these discs, and disposed such that a back surface of the second input disc is opposed to a back surface of the first input disc, a tubular back surface cylinder wall is provided on each of the back surfaces of the first input disc and the second input disc so as to project therefrom.

Growing community of inventors

Kobe, Japan

Tatsuhiko Goi