Fluid adjustment device and aircraft

Patent metadata

Field	Value
Publication number	US-2022185457-A1
Application number	US-201917418025-A
Country	US
Kind code	A1
Filing date	Dec 26, 2019
Priority date	Jan 31, 2019
Publication date	Jun 16, 2022
Grant date	—

Abstract

A fluid adjustment device is provided with: a body part mounted on a wing tip, which is an end part of a main wing on the opposite side to the wing root, and having an upper opening and a lower opening formed in an upper surface of the body part and a lower surface of the body part; a first Francis turbine that sucks air from the upper opening and the lower opening and discharges the sucked air from the trailing edge side of the main wing; and a first motor for rotating the first Francis turbine in a direction opposite to a rotation direction of a wingtip vortex generated at the wingtip. The first Francis turbine has a central axis extending from the leading edge of the main wing toward the trailing edge, sucks air from the circumferential direction, and discharges the sucked air in the axial direction.

First claim

1 . A fluid adjustment device comprising:
a body part that is provided at a wing tip, which is an end portion opposite to a wing root of a wing, and includes a suction opening formed in one or both of a pressure surface and a suction surface; a first fan that sucks air from the suction opening and discharges the sucked air from a trailing edge side of the wing; and a first drive unit that rotates the first fan in a direction opposite to a rotation direction of wingtip vortices generated at the wing tip.

2 . The fluid adjustment device according to claim 1 ,
wherein the first fan is a Francis turbine of which a central axis extends in a direction from a leading edge to a trailing edge of the wing, that sucks air from a circumferential direction, and that discharges the sucked air in an axial direction.

3 . The fluid adjustment device according to claim 1 ,
wherein the first fan includes
a cross flow fan of which a central axis extends in a direction from a leading edge to a trailing edge of the wing, that sucks air from a circumferential direction, and that discharges the air in the circumferential direction, and
a duct that guides the air discharged from the cross flow fan to the trailing edge side of the wing.

4 . The fluid adjustment device according to claim 1 , further comprising:
a second fan that extends in a wing spanwise direction of the wing, is provided along a trailing edge of the wing, sucks air along one or both of the pressure surface and the suction surface of the wing, and discharges the sucked air to a turbine; and a second drive unit that rotationally drives the second fan, wherein the first drive unit is the turbine that is provided at an end portion of the first fan in an axial direction and is rotationally driven by means of the air discharged from the second fan.

5 . An aircraft comprising:
the fluid adjustment device according to claim 1 .

6 . The fluid adjustment device according to claim 2 , further comprising:
a second fan that extends in a wing spanwise direction of the wing, is provided along a trailing edge of the wing, sucks air along one or both of the pressure surface and the suction surface of the wing, and discharges the sucked air to a turbine; and a second drive unit that rotationally drives the second fan, wherein the first drive unit is the turbine that is provided at an end portion of the first fan in an axial direction and is rotationally driven by means of the air discharged from the second fan.

7 . The fluid adjustment device according to claim 3 , further comprising:
a second fan that extends in a wing spanwise direction of the wing, is provided along a trailing edge of the wing, sucks air along one or both of the pressure surface and the suction surface of the wing, and discharges the sucked air to a turbine; and a second drive unit that rotationally drives the second fan, wherein the first drive unit is the turbine that is provided at an end portion of the first fan in an axial direction and is rotationally driven by means of the air discharged from the second fan.

Assignees

• Mitsubishi Heavy Ind Ltd

Inventors

• Morisaki Yuki
• Saiki Yasuhiro
• Imai Kazuhiro

Classifications

• F03B3/02

  with radial flow at high-pressure side and axial flow at low-pressure side of rotors, e.g. Francis turbines {(rotors per se F03B3/125)} · CPC title

• B64C23/065 Primary

  at the wing tips · CPC title

• B64C3/32

  specially adapted for mounting power plant · CPC title

• B64C3/00

  Wings (ornithopter wings B64C33/02) · CPC title

• B64C21/025 Primary

  for simultaneous blowing and sucking · CPC title