Load Distribution Panel Assembly for Gas Turbine Thrust Reversers
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Solution Overview
Problem
Existing load distribution systems in aircraft thrust reversers face challenges in uniformly distributing point loads due to complex designs and heavy weight requirements, leading to increased structural reinforcement and complexity, which in turn increase weight and cost.
Innovation Solution
A load distribution panel assembly with a circumferential structural panel featuring a compliant barrel portion and a stiffened bulb portion with a filled core, converting fore/aft point loads into hoop tension and compression loads, thereby uniformly distributing loads without the need for extensive structural reinforcement.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If large metallic fittings and thick composite laminates are used to control deflections induced by point loads, then load distribution and structural strength are improved, but weight increases significantly
Solution Approach 1:
The patent employs a hybrid composite structure combining metallic fittings with composite laminates in a load distribution panel. This composite approach allows the structure to achieve required strength and stiffness while reducing overall weight compared to purely metallic solutions, as the composite materials provide high strength-to-weight ratio and can be tailored to specific load paths
Solution Approach 2:
The load distribution panel features variable thickness and material distribution, with thicker reinforcement localized at high-stress areas (such as near load application points) and thinner sections in low-stress areas. This local quality approach ensures structural strength is provided only where needed, minimizing unnecessary weight throughout the entire component
2Stability of the object's composition
If secondary stiffening features are added to control deflection away from the load application point, then structural stability is improved, but weight and part count increase
Solution Approach 1:
The patent integrates secondary stiffening features directly into the load distribution panel as monolithic or co-cured structures rather than adding them as separate components. The stiffening elements (such as ribs or bulkheads) are merged with the panel itself, providing structural stability while reducing part count and assembly complexity
Solution Approach 2:
The stiffening features are constructed using composite materials with optimized fiber orientations and stacking sequences to provide maximum stiffness and stability with minimum weight. The composite construction allows for tailored mechanical properties that match the specific stabilization requirements of each region
3Reliability
If extensive structural reinforcement is used to overcome load offset between actuators and fixed engine structure, then load distribution uniformity is improved, but device complexity increases
Solution Approach 1:
The load distribution panel serves as an intermediary structural element between the thrust reverser actuators and the fixed engine structure. It mediates the load transfer by distributing point loads from the actuators across a broader area of the engine structure, achieving uniform load distribution while maintaining a relatively simple single-panel design rather than complex multi-component reinforcement systems
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 provides efficient and uniform load distribution with reduced structural reinforcement, complexity, and weight, enhancing the performance and cost-effectiveness of aircraft thrust reversers.
Implementation Method 1
a first compliant portion (80), comprising a compliant barrel portion (80a)... The load distribution panel assembly converts one or more fore/aft point loads (142) applied to the load distribution panel assembly... to a hoop tension load (152) and a hoop compression load (154)
Implementation Method 2
The second stiffened portion (82)... has a closed stiffened cavity portion (87a) integral with a perimeter lip portion (87b)... comprising a filled core interior (118a) filled with a stiffened material (120)
Data Source
Figure 1
Figure 2A
Figure 2B
AI summary
There is provided a load distribution panel assembly (60) for a gas turbine engine. The assembly has a panel structure (61) having at least one circumferential structural panel (70) having a first end (74a), and a second end (74b), the first end coupled to a fixed structure (76) of the gas turbine engine. The circumferential structural panel (70) has a first compliant portion (80) extending away from the first end, and has a second stiffened portion (82) angled with respect to and extending radially away from the first compliant portion (80), and terminating at the second end. The second stiffened portion (82) has a closed stiffened cavity portion (87a) integral with a perimeter lip portion (87b). The panel assembly converts fore/aft point load(s) (142) applied to it by load applying apparatus(es) (50), to hoop tension load (152) and hoop compression load (154), and reacts a load offset (146) in in-plane load(s), to provide uniform load distribution (156) of the fore/aft point load(s) (142) to the fixed structure (76).