Thrust Link-Lever Mount With Adjustable Fulcrum
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Solution Overview
Problem
Aircraft engine mounting systems face challenges in reducing engine deflection and bending, which can lead to blade tip rub encounters and increased specific fuel consumption, due to the transfer of various loads such as weight, axial thrust, and lateral forces.
Innovation Solution
The implementation of a thrust mount assembly with a laterally offset and adjustable fulcrum position in the engine-mounting linkage system, which includes a thrust link-lever and thrust links, allows for the balancing of loads and reduction in engine deflection by adjusting the lever arms to counteract bending moments.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If conventional engine mounts are used to transfer loads, then the engine support structure can handle the loads, but engine deflection and bending increase leading to blade tip rub encounters
Solution Approach 1:
The patent applies asymmetry by laterally offsetting the fulcrum position of the thrust link-lever from the engine's axis of rotation. This creates unequal lever arms on either side of the fulcrum, allowing differential load distribution that actively counteracts bending moments and reduces engine frame deflection, thereby maintaining proper blade tip clearances
Solution Approach 2:
The patent implements dynamics by making the fulcrum position laterally adjustable relative to the engine's axis of rotation. This adjustability allows the engine mounting system to adapt to different operating conditions and load scenarios, optimizing the balance between thrust load transfer and bending moment counteraction for improved reliability
2Reliability
If larger blade tip clearances are maintained to avoid rub encounters, then blade tip rub is prevented, but engine specific fuel consumption increases
Solution Approach 1:
By using an asymmetric fulcrum offset configuration, the patent reduces engine frame deflection and bending, which maintains narrower blade tip clearances without causing rub encounters. This allows the engine to operate with optimized clearances that improve aerodynamic efficiency and reduce specific fuel consumption
Solution Approach 2:
The patent applies preliminary action by proactively counteracting bending moments through the offset fulcrum configuration before they can cause excessive deflection. This preventive approach maintains optimal blade tip clearances throughout operation, avoiding the need for larger clearance margins that would increase fuel consumption
3Stability of the object's composition
If the fulcrum position is laterally offset to balance loads, then engine deflection is reduced, but the mounting system complexity increases
Solution Approach 1:
The thrust link-lever assembly serves multiple functions: it transfers thrust loads from the engine, counteracts bending moments through offset fulcrum, and provides adjustable positioning. This multi-functionality reduces the need for separate components, thereby limiting the increase in overall system complexity while achieving deflection reduction
4Reliability
If the fulcrum position is made adjustable to optimize load balancing, then load balancing improves, but the ease of operation and maintenance decreases
Solution Approach 1:
The patent implements dynamics by providing lateral adjustability of the fulcrum position, allowing the mounting system to be optimized for different operating conditions and load scenarios. This adjustability improves load balancing and reliability while maintaining practical operability through designed adjustment mechanisms
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 reduces engine deflection and bending, thereby minimizing blade tip rub encounters and improving specific fuel consumption by optimizing the engine's operational clearances and structural integrity.
Implementation Method 1
The thrust link-lever may include a laterally offset fulcrum position, such that a right-side lever arm defined from the fulcrum position and extending towards a right-side thrust link differs from a left-side lever arm defined from the fulcrum position and extending towards a left-side thrust link
Data Source
AI summary
A thrust mount assembly includes a thrust link-lever that has a first end region, a second end region, and a fulcrum region disposed between the first end region and the second end region. A thrust link-lever may be coupled or couplable to a fulcrum body of an aft engine-mount at a fulcrum position of the thrust link-lever. When coupled to a turbomachine, the fulcrum position of the thrust link-lever may be laterally offset and/or laterally adjustable relative to an axis of rotation of the turbomachine. A load translated from an engine frame of a turbomachine to an engine-mounting linkage system may be determined and a fulcrum position for the thrust mount assembly may be adjusted laterally relative to an axis of rotation of the turbomachine.