Aircraft Engine Lubrication Circuit With Variable-Section Jet Pump
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Solution Overview
Problem
The existing lubrication systems for aeronautical engines and reduction gearboxes are complex and cumbersome, making it difficult to precisely meter and distribute lubricating oil effectively, leading to inefficient lubrication.
Innovation Solution
A system with a jet pump of variable section is introduced between the first and second supply pumps, allowing for modulation of the suction flow and recovery of hydraulic energy, with an electronic control unit to calculate and control oil flow rates to ensure precise lubrication needs are met.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If a four-way valve is used to distribute oil to the aeronautical engine and reduction gearbox, then oil flow can be regulated to different enclosures, but the system becomes complex and cumbersome
Solution Approach 1:
The patent extracts the complex four-way valve distribution system and replaces it with two independent supply pumps, each dedicated to a specific lubrication circuit. This eliminates the need for complex valve mechanisms while maintaining the ability to regulate oil flow to different enclosures independently.
Solution Approach 2:
The lubrication system is segmented into two independent circuits with separate supply pumps (first supply pump for reduction gearbox, second supply pump for aeronautical engine). Each pump can be controlled independently, simplifying the overall system architecture while maintaining adaptability.
2Adaptability or versatility
If separate lubrication circuits are implemented for the reduction gearbox and aeronautical engine, then each can be lubricated independently, but the system becomes more complex
Solution Approach 1:
The system is divided into two independent lubrication circuits, each with its own supply pump. The first supply pump serves the reduction gearbox circuit, while the second supply pump serves the aeronautical engine circuit. This segmentation allows independent control and simplifies the overall system by eliminating the need for complex valve arrangements.
3Device complexity
If a single supply pump is used for both lubrication circuits, then the system is simpler, but precise metering of oil flow to each enclosure becomes difficult
Solution Approach 1:
Instead of using a single supply pump, the patent implements two separate supply pumps, each dedicated to a specific lubrication circuit. This segmentation enables precise metering of oil flow to each enclosure independently, as each pump can be controlled separately to deliver the exact flow rate required by its respective circuit.
Solution Approach 2:
The patent introduces independent supply pumps as intermediary devices between the oil reservoir and each lubrication circuit. These pumps act as mediators that can precisely control and meter the oil flow to each enclosure, ensuring accurate lubrication while maintaining system simplicity.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
This solution simplifies the lubrication system by allowing fairer oil distribution, reducing power consumption, and preventing cavitation, thereby extending pump lifespan and improving lubrication efficiency without modifying existing circuits.
Implementation Method 1
the second circuit comprises a jet pump of variable section powered at least by said first supply pump bypassing the first circuit
Implementation Method 2
allowing for modulation of the suction flow and recovery of hydraulic energy
Implementation Method 3
jet pump of variable section allowing for modulation of the suction flow
Data Source
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AI summary
The invention relates to a system (1) for lubricating an aeronautical engine (5) and a reduction gearbox (4) associated with the engine (5), the system (1) comprising an oil reservoir (2) feeding at least one first supply pump (3) supplying a first circuit (6) of the gearbox (4) opening into at least one chamber (4a) of the gearbox (4) and, in parallel, a second circuit (7) of the engine (5) opening into chambers (5a) of the engine (5). The second circuit (7) comprises a jet pump (9) of variable cross section supplied at least by the first supply pump (3), bypassing the first circuit (6), a second driven supply pump (10) being integrated into the second circuit (7) downstream of the jet pump (9), a portion of a flow (Qp) in the first circuit (6) being drawn off by the jet pump (9) to supply the second circuit (7).