Fluid scavenge system
AssigneeTextron Innovations Inc.
InventorsDouglas Robert Mueller, Ivan Russell Laric
Life of this patent
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Abstract
A fluid pump system for an aircraft has a rotatable component having first and second fluid ports, each port in fluid communication with a selected interior portion of the component, the portions being spaced from each other. A valve controls allows a first flow rate through the first fluid port and allows a second flow rate through the second fluid port when the component is in a first angular orientation. The valve allows a third flow rate through the first fluid port and allows a fourth flow rate through the second fluid port when the component is in a second angular orientation.
Claims16
A fluid pump system for an aircraft, the system comprising:
- a gearbox component for a rotor, the component being pivotable between an airplane-mode orientation and a helicopter-mode orientation and having first and second fluid scavenge ports, each scavenge port in fluid communication with a selected interior portion of a fluid sump of the component for withdrawing fluid from the associated portion of the sump, the portions being spaced from each other;
- and
- a valve for controlling a flow rate of fluid through each scavenge port;
- wherein the valve allows a first flow rate through the first scavenge port and allows a second flow rate through the second scavenge port when the component is in a first angular orientation;
- and
- wherein the valve allows a third flow rate through the first scavenge port and allows a fourth flow rate through the second scavenge port when the component is in a second angular orientation.
A fluid scavenge system for an aircraft, the system comprising:
- a gearbox component for a rotor, the component being pivotable between an airplane-mode orientation and a helicopter-mode orientation and having a sump therein configured for retaining a volume of fluid;
- first and second scavenge ports, each port in fluid communication with a selected portion of the sump for withdrawing fluid from the associated portion of the sump, the portions being spaced from each other;
- and
- a valve for controlling a flow of fluid through each scavenge port;
- wherein the valve allows flow through the first scavenge port and prevents flow through the second scavenge port when the component is in a first orientation;
- and
- wherein the valve prevents flow through the first scavenge port and allows flow through the second scavenge port when the component is in a second orientation.
A lubricant scavenge system for a gearbox of a tiltrotor aircraft, the gearbox being pivotable between an airplane-mode orientation and a helicopter-mode orientation and having a fluid sump therein, the system comprising:
- first and second scavenge ports, each port in fluid communication with a selected portion of the sump for withdrawing fluid from the associated portion of the sump, the portions being spaced from each other;
- and
- a valve for controlling a flow of fluid through each scavenge port;
- wherein the valve allows a first flow rate through the first scavenge port and allows a second flow rate through the second scavenge port when the gearbox is in a first angular orientation;
- and
- wherein the valve allows a third flow rate through the first scavenge port and allows a fourth flow rate through the second scavenge port when the gearbox is in a second angular orientation.
Dependencies are inferred from the claim text.