Gas Turbine Engine Backbone Bending Reduction via Linkage
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Solution Overview
Problem
Gas turbine engines experience backbone bending due to the thrust loads transmitted from the engine to the pylon, leading to stress and wear on the engine components and affecting blade clearances and engine efficiency.
Innovation Solution
A mechanical linkage with a bending restraint is introduced to connect the fan section of the gas turbine engine to the pylon, using joints such as pin joints or whiffletree joints to react forces and prevent backbone bending.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If the engine is mounted to the pylon using conventional rigid mounting, then the engine is securely supported, but backbone bending occurs due to thrust loads causing stress and wear on engine components
Solution Approach 1:
The mounting system is segmented into multiple independent linkages (first linkage, second linkage, third linkage) that connect the engine to the pylon at different locations. Each linkage independently supports specific forces, dividing the backbone bending stress into manageable components that are distributed across multiple mounting points rather than concentrated on the engine backbone.
Solution Approach 2:
The patent introduces external linkages as intermediary structures between the engine and the pylon. These linkages act as mediators that bear and transmit thrust loads and bending forces directly to the pylon structure, preventing these forces from being transmitted through the engine backbone and causing stress and wear on engine components.
2Stability of the object's composition
If rigid mounting is used to securely support the engine, then structural stability is maintained, but blade clearances are affected due to backbone bending
Solution Approach 1:
The mounting system is divided into multiple specialized linkages, each responsible for specific functions: some linkages maintain structural stability while others specifically address blade clearance requirements by preventing backbone bending in directions that would affect clearance. This segmentation allows independent optimization of stability and clearance precision.
Solution Approach 2:
Different linkages are positioned and configured to provide localized support where needed. The linkages are arranged to specifically prevent backbone bending in regions that would affect blade clearances, while maintaining overall structural stability. This local quality approach ensures that blade clearance precision is maintained without compromising overall engine stability.
3Power
If conventional mounting is used, then the engine is supported, but engine efficiency decreases due to backbone bending
Solution Approach 1:
The external linkages serve as intermediary structures that bear the thrust loads and bending forces, preventing these forces from deforming the engine backbone. By eliminating backbone bending, the linkages prevent energy losses associated with structural deformation and vibration, allowing the engine to operate more efficiently and convert more energy into useful thrust output.
Solution Approach 2:
The linkages are pre-configured to counteract backbone bending forces before they can cause energy losses. By providing preliminary structural support and force distribution, the linkages prevent the development of bending moments that would otherwise consume energy and reduce engine efficiency, ensuring optimal power output from the outset.
Data Source
AI summary
Methods, apparatus, systems and articles of manufacture are disclosed. An apparatus for mounting a gas turbine engine to a pylon includes: a thrust link coupled to the gas turbine engine and an aft mount, the gas turbine engine coupled to the pylon via a forward mount and the aft mount, a bending restraint having a first end and a second end, the bending restraint including an actuator positioned at the first end to apply a force to a fan section of the gas turbine engine, a first joint positioned at the first end of the bending restraint, the first joint coupled to the first end of the bending restraint and the fan section, and a second joint positioned at the second end of the bending restraint, the second joint coupled to the second end of the bending restraint.