Planet Gear Lubricating Core for Oil Recirculation Control

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Solution Overview

Problem

Current mechanical reduction gears in turbine engines face inefficiencies in oil circulation and particle evacuation, leading to recirculation and energy loss, and require complex structures and multiple components for lubrication and cooling.

Innovation Solution

The introduction of a deflector with protruding tabs inserted into inter-helical grooves of planet gears to prevent oil recirculation, combined with a lubricating and cooling core that uses coaxial frusto-conical shields for oil circulation and a distributor with independent oil circuits for efficient lubrication and cooling, simplifying the structure and reducing components.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Reliability

If conventional lubrication systems are used in reduction gears, then oil circulation is maintained, but oil recirculation occurs and particle evacuation is inefficient

Engineering Contradiction:

Improveparticle evacuation efficiencyVSAvoidenergy loss from oil recirculation

Core Design Contradiction:

ReliabilityVSLoss of energy

Solution Approach 1:

The lubrication system is segmented into distinct functional zones using deflectors with tabs that divide the oil flow paths. The deflectors create separate circulation zones that prevent mixed flow and ensure efficient particle evacuation while eliminating energy-wasting recirculation loops.

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

Deflectors with protruding tabs serve as intermediary elements that mediate between the oil supply and the gear contact zones. These deflectors guide oil flow in specific directions, prevent recirculation, and facilitate particle removal without requiring complex additional components.

Inventive Principle:

Principle #24Intermediary (Mediator)

2Reliability

If multiple components are used for lubrication and cooling, then lubrication coverage is improved, but device complexity increases

Engineering Contradiction:

Improvelubrication coverageVSAvoidnumber of components

Core Design Contradiction:

ReliabilityVSDevice complexity

Solution Approach 1:

The deflectors with protruding tabs perform multiple functions simultaneously: they guide oil flow to ensure proper lubrication coverage, prevent oil recirculation, and facilitate particle evacuation. This multi-functionality eliminates the need for separate components for each function, reducing overall device complexity.

Inventive Principle:

Principle #6Universality (Multi-functionality)

Solution Approach 2:

The lubrication and cooling functions are merged into a single integrated oil circulation system. The deflectors combine flow guidance, recirculation prevention, and particle evacuation capabilities into one component, reducing the number of separate parts needed while maintaining comprehensive lubrication coverage.

Inventive Principle:

Principle #5Merging (Combining)

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 enhances oil circulation and particle evacuation, reduces energy loss, and simplifies the structure by preventing oil recirculation, improving the mechanical efficiency and reliability of turbine engines while reducing the number of components and assembly steps.

Implementation Method 1

the shields being configured to extend inside the axle and to cover at least a radially internal surface of the axle to define with the latter at least one annular cavity for the circulation of oil for lubricating and cooling the axle

Methodology Applied

Scientific EffectFluid circulation:

Implementation Method 2

circulation of oil for lubricating and cooling the axle

Methodology Applied

Scientific EffectLubrication: Lubrication

Data Source

PatentUS11339869B2Lubricating and cooling core for a mechanical reduction gear of an aircraft turbine engine

Publication Date: 2022.05.24 SAFRAN TRANSMISSION SYST

AI summary

A lubricating and cooling core for a mechanical reduction gear of a turbine engine, for example of an aircraft, is configured to be mounted in an axis of a planet gear of the reduction gear. The core includes first and second coaxial and substantially frusto-conical shields, each having a first end with a greater diameter and a second opposite end with a smaller diameter, the shields being secured to one another by their second ends and being configured to extend inside the axis and to cover at least a radially internal surface of the axis to define with the latter at least one annular cavity for the circulation of oil for lubricating and cooling the axis, the second ends of the first and second shields having fluid connection means configured to connect the at least one cavity to a source of lubricating and cooling oil.