Mitsubishi Aircraft Corporation

Mitsubishi Heavy Industries Limited

Tadahiko Suzuta

Nobuhide Hara

Hiroyuki Yamamoto

Ichiro Maeda

Kei Takao

Yoshiyuki Kondo

Toshiyuki Mizutani

Atsushi Imai

Koichi Tanimoto

Kentaro Hayashi

Takuo Oda

Hiroyuki Nakaharai

Yuichi Otani

Hiroko Kitamoto

Kengo Shimamura

Toshiyuki Umemoto

Naoaki Hirota

Yasuhiko Hirao

Hideyuki Kudo

Sumiu Uchida

Yosuke Katsura

A cooling system of the present disclosure includes: a coolant tank storing a coolant removing heat from a heating element in a closed space as an inner space; a plurality of heat pipes that are arranged to extend from the coolant tank toward the outside of the coolant tank and respectively having passages allowing the coolant as a working fluid to be movable therethrough; and a blower fan blowing air to the plurality of heat pipes from the outside of the coolant tank in a direction in which the heat pipes are arranged, wherein a cross-sectional shape orthogonal to the extension direction of each heat pipe is a flat plate shape having a leading edge on an upstream side of a blowing direction of the blower fan and a trailing edge on a downstream side thereof with the blowing direction as a longitudinal direction.

Cooling system

A heat exchanger includes a pipe main body forming a flow path to which a first fluid is supplied, a pair of partition plates defining an enclosed space, a plurality of heat transfer tubes, a supply portion configured to supply a second fluid into the enclosed space, a discharge portion configured to discharge the second fluid in the enclosed space, and a flow path forming portion forming a plurality of small flow path portions between the heat transfer tubes adjacent to each other. The second fluid flows between the plurality of heat transfer tubes in the enclosed space in a direction opposite to the flow direction of the first fluid. The plurality of small flow path portions are disposed at positions different from each other in an extension direction when viewed from a position where the discharge portion is disposed.

Heat exchanger

Temperature of a structural member is maintained at allowable temperature or less by suppressing heat transfer from a high-temperature duct to the structural member. An insertion sheet according to the present invention is inserted between a flange and a partition panel. The flange is provided on a bleed duct and is fastened to the partition panel. The bleed duct penetrates through a partition wall of an aircraft. The insertion sheet includes first parts and a second part. The first parts are disposed near respective shafts of rivets provided at a plurality of positions of the insertion sheet. The second part extends among the first parts. The first parts bear a load of fastening, and the second part has thermal conductivity lower than thermal conductivity of the first parts.

Insertion sheet between high-temperature duct and structural member of aircraft, duct of aircraft, and aircraft

The present invention provides a pipe structure including: a pipe through which a gaseous body having a higher temperature than a temperature of a surrounding atmosphere flows; a cover that covers an outer peripheral portion of the pipe, and defines a plurality of vents from which the gaseous body leaking from the pipe flows out; and a line-shaped sensor that passes a position corresponding to each of the plurality of vents, and is sensitive to a temperature or a concentration of the gaseous body outside the cover, wherein the sensor includes a range in which the sensor rises upward from the position corresponding to the vent.

Pipe structure and aircraft

The present invention provides a pipe structure including: a pipe through which a gaseous body having a higher temperature than a temperature of a surrounding atmosphere flows; a cover that covers an outer peripheral portion of the pipe, and defines a plurality of vents from which the gaseous body leaking from the pipe flows out; and a guide member that guides the gaseous body flowing out from the vent toward a line-shaped sensor that passes a position corresponding to each of the plurality of vents, and is sensitive to a temperature or a concentration of a gaseous body outside the cover.

The present invention provides a pipe structure including a pipe that is disposed along an approximately horizontal direction, and has a plurality of ducts through which a gaseous body having a higher temperature than a temperature of a surrounding atmosphere continuously flows, and a plurality of couplings each connecting the ducts together; and a cover covering an outer periphery of the pipe. The cover defines a plurality of vents from which the gaseous body leaking from the pipe flows out of the cover at an interval in a length direction of the pipe. As the plurality of vents, the cover includes at least first vents located corresponding to the couplings. Respective positions of the first vents are substantially set within a range from a two o'clock position to a ten o'clock position through a six o'clock position in a cross sectional surface of the cover.

Pipe structure, aircraft, and method for giving robustness to leak detection

An aircraft includes: a fairing which covers a lower part of a fuselage having a main landing gear bay (MLG bay), and defines a ventilation cavity communicating with the MLG bay between the fairing and the fuselage; and a heat removal system which removes heat generated from the MLG inside the MLG bay to the outside of the MLG bay by suctioning/discharging air through an inlet port and an outlet port leading from the ventilation cavity or the MLG bay to external air. The fairing defines a wheel opening through which a wheel of the MLG enters and exits, and defines a ventilation port, which functions as one of the inlet and outlet ports, between the fairing and an outer peripheral part of the wheel exposed from the wheel opening to the lower side of the MLG bay when the MLG is retracted.

Heat removal structure of aircraft main landing gear bay

In a steam-water separator, a swirl vane () is provided inside a riser (), an annular downcomer space () is formed by providing a downcomer barrel () outside the riser (), a deck plate () is arranged above the riser () and the downcomer barrel () with a predetermined space therefrom, an orifice () and vents () are formed, and aperture ratios of plural slits (, and) formed on the riser () are set at from 30% to 70%. Accordingly, the steam and the water is appropriately separated, and the separated steam is reliably discharged upward from the orifice while the separated water is allowed to reliably flow down through the downcomer space, thereby enhancing steam-water separating efficiency.

Steam-water separator

In a steam-water separator, horizontal slits are formed on the outer side of the curving direction of the curved part and at a location between the curved part of the riser and the swirl vane.

Growing community of inventors

Tokyo, Japan

Tadahiko Suzuta