Aeronautical Engine Lubrication With Variable-Section Jet Pump Control
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Solution Overview
Problem
The existing lubrication systems for aeronautical engines and reduction gearboxes are complex and difficult to regulate, making it challenging to precisely dose the quantity of oil for effective lubrication, leading to inefficiencies and potential damage from cavitation at high altitudes.
Innovation Solution
A system incorporating a variable-section jet pump between the first and second supply pumps, which modulates the flow rate by recovering hydraulic energy and using an electronic control unit to calculate and control the oil flow rates, ensuring precise distribution to the aeronautical engine and reduction gearbox, thereby simplifying the lubrication process and reducing power consumption.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If a four-way valve is used to distribute oil to the aeronautical engine and reduction gearbox, then the lubrication can be regulated, but the system becomes complex and bulky
Solution Approach 1:
The patent removes the complex four-way valve from the system and replaces it with a simpler distribution mechanism. The oil supply pump directly distributes oil to both the aeronautical engine and reduction gearbox through separate circuits, eliminating the need for complex valve-based flow regulation while maintaining the ability to supply both components.
Solution Approach 2:
The oil supply pump performs multiple functions: it supplies oil to the aeronautical engine, supplies oil to the reduction gearbox, and regulates flow to both circuits simultaneously. This multi-functional approach eliminates the need for separate control valves for each circuit, simplifying the overall system architecture.
2Adaptability or versatility
If separate lubrication circuits are used for the aeronautical engine and reduction gearbox, then each can be lubricated independently, but the system becomes more complex
Solution Approach 1:
The patent divides the lubrication system into two separate circuits: one circuit supplies the aeronautical engine and another circuit supplies the reduction gearbox. Each circuit is controlled independently from the oil supply pump, allowing independent regulation of oil flow to each component while maintaining a relatively simple overall structure.
3Device complexity
If fixed flow rate pumps are used, then the lubrication system is simple, but the oil flow rate cannot be precisely dosed for different operating conditions
Solution Approach 1:
The patent employs an oil supply pump with variable flow rate capability that can dynamically adjust the amount of oil supplied to both the aeronautical engine and reduction gearbox. This dynamic adjustment allows precise dosing of oil flow rates according to different operating conditions, speeds, and temperature requirements while maintaining a relatively simple pump-based system architecture.
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
The system achieves precise and efficient lubrication by regulating oil flow rates to meet the needs of both the aeronautical engine and reduction gearbox, reducing the risk of cavitation and improving power efficiency without modifying existing lubrication circuits.
Implementation Method 1
a variable-section jet pump supplied at least by said at least one first supply pump bypassing the first circuit, a second driven supply pump being integrated into the second circuit downstream of the variable-section jet pump, a part of a flow rate in the first circuit being collected by the variable-section jet pump to supply the second circuit
Data Source
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).