Ventilvorrichtung zur Steuerung eines Fluidstroms durch einen Kanal oder eine Öffnung einer Klimaanlage eines Flugzeuges

Details

Veröffentlichungs-Nr.

EP3998210

Aktenzeichen

EP21158207

Anmeldetag

19. Februar 2021

Veröffentlichung

13. September 2023

Erteilung

13. September 2023

Rechtsraum

EP

IPC

B64D13/00F16K1/36F16K1/42F16K31/10F16K31/06F24F13/10

Abstract

Valve apparatus for controlling fluid flow through a duct of an air conditioning system of an aircraft, the valve apparatus comprising:• a valve seat body (2) having a valve seat hole (3) being configured to allow the fluid to flow through it,• a damper body (4) for closing the valve seat hole (3),• wherein the valve seat body (2) and the damper body (4) are movable relative to each other between an open configuration and a closed configuration, wherein in the open configuration the fluid may flow through the valve seat hole (3) and in the closed configuration the damper body (4) interacts with the valve seat body (2) in a sealing manner such that the fluid may not flow through the valve seat hole (3),• wherein the valve seat hole (3) has a hole contour formed by a hole edge (5) and the damper body has a damper contour formed by a damper edge (6), the hole edge and the damper edge being configured to interact with each other in the sealing manner thereby forming a circumferential sealing line having a circumferential sealing length,• wherein the hole contour has a plurality of hole protuberances (7) and the damper contour has a plurality of damper protrusions (8), so that the circumferential sealing length is larger than a reference length being defined by a length of a circumference of an equal area circle (EAC) having an area equal to an area of the valve seat hole (3),• wherein the valve apparatus comprises a solenoid actuator (9) having an actuator rod for transmitting an actuator force, the solenoid actuator being mounted for moving the damper body (4) relative to the valve seat body (2) towards the closed or open configuration, and• wherein force transmission means (11) are arranged between the actuator rod (10) and the damper body (4), the force transmission (11) means being configured to apply a closing force to the damper body that is larger than the actuator force.

Anmelder

Firma

Lilium eAircraft GmbH

Land

🇩🇪 Deutschland

Fachgebiete