U-Shaped Preforms for Deep-Blade Aircraft Thrust Reverser Grids
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Solution Overview
Problem
Existing methods for producing grids of blades for aircraft thrust reversing devices result in high mass and energy consumption due to the complex geometry and difficulty in extracting blades with large depths using simple cores.
Innovation Solution
A method involving the production and assembly of U-shape preforms, each comprising a central part and branches forming longitudinal walls, allows for blades with large depths while using simple tooling by eliminating undercuts and ensuring structural integrity through compression and polymerization phases.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Shape
If traditional molding methods with cores are used to produce grids of blades, then the blades can be formed with required geometry, but the extraction of blades with large depths becomes difficult and requires complex sliding cores
Solution Approach 1:
The invention divides the grid of blades into multiple separable rows, where each row can be extracted independently from the mold. This segmentation eliminates the need for complex sliding cores to extract deep blade structures, as each row is removed separately through simplified extraction paths.
Solution Approach 2:
Instead of forming the entire grid as a single monolithic structure that requires complex extraction, the invention inverts the approach by creating individual blade rows that can be easily removed. The mold design allows rows to be extracted in reverse sequence of insertion, simplifying the extraction mechanism.
2Reliability
If a large number of cells are included in the grid of blades to achieve the required geometry, then the functional performance is improved, but the mass of the structure increases significantly
Solution Approach 1:
The invention applies local quality by varying the blade depth and cell structure in different regions of the grid. Blades with larger depths are positioned where maximum thrust reversal effect is needed, while areas requiring less functionality have reduced blade depths, optimizing the mass-performance ratio.
Solution Approach 2:
The invention uses partial action by implementing blades with varying depths rather than uniform maximum depth throughout the entire grid. This allows the structure to achieve sufficient functional performance with reduced overall mass by applying blade depth only where necessary.
3Weight of moving object
If the blades are made with small depth to reduce mass, then the onboard mass is reduced, but the number of cells and overall complexity increases
Solution Approach 1:
The invention implements local quality by varying blade depth according to functional requirements in different grid regions. This allows reduction of overall mass through selective use of deeper blades only where maximum thrust reversal effect is required, while other areas use shallower blades to reduce mass.
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
Enables the production of blades with large depths, reducing mass and energy consumption, and simplifies the extraction process by using U-shape preforms with no undercuts, thus improving the efficiency and feasibility of manufacturing.
Implementation Method 1
a consolidation or polymerization step to connect the first and second preforms together during which the assembly is compressed and subjected to an increase in temperature
Implementation Method 2
a consolidation or polymerization step to connect the first and second preforms together during which the assembly is compressed and subjected to an increase in temperature
Implementation Method 3
The rise in temperature causes expansion of the cores 52 which compress the second preforms 48′
Implementation Method 4
After the consolidation or polymerization step the grid of blades 44 obtained and the cores 52 are cooled, which causes the cores 52 to shrink
Data Source
AI summary
A method of obtaining a grid of blades of an aircraft thrust reversing device by producing U-shape elements each including an integral central part corresponding to a blade and first and second branches each corresponding to at least a part of a longitudinal wall of the grid of blades and assembling which includes connecting the first branches of the various U-shape elements to one another in such a manner as to form a first longitudinal wall and connecting the second branches of the various U-shape elements to one another in such a manner as to form a second longitudinal wall.