Turbojet Engine Reinforcing Structures Limit Casing Flexion
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Solution Overview
Problem
Prior aircraft engine assemblies experience deformation and performance loss due to flexion in the fan and central casings under thrust and inertial forces, leading to clearance issues and reduced engine efficiency.
Innovation Solution
The introduction of an annular load-transfer structure mechanically connected to the central casing, with reinforcing structures forming shear planes associated with the front engine mounts, which are connected to the fan casing and structural arms, to rigidify the engine and limit flexion.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If the fan casing and central casing are connected by structural arms without additional reinforcing structures, then the device complexity is reduced, but the casings deform and flex under thrust and inertial forces, leading to performance loss
Solution Approach 1:
The patent introduces reinforcing structures that extend in the longitudinal direction (another dimension) between the fan casing and central casing. These structures add structural support along the length of the engine, preventing casing flexion and deformation without requiring complex modifications to the existing radial structural arm configuration.
Solution Approach 2:
The reinforcing structures are integrated with the existing structural arms to form a composite load-bearing system. This combination of reinforcing structures and structural arms creates a more rigid framework that resists thrust and inertial forces while maintaining the original structural design philosophy.
2Ease of operation
If diametrically opposed engine mounts are used to facilitate thrust force transmission, then the ease of operation is improved, but a torque is introduced that deforms the engine casing
Solution Approach 1:
The patent positions the engine mounts at specific locations that are not diametrically opposed, but rather at angles that optimize both thrust transmission and torque minimization. This local optimization of mount positioning allows effective force transmission while avoiding the detrimental effects of offset mounting that cause casing deformation.
3Device complexity
If the central casing is left unsupported to maintain structural simplicity, then the device complexity is reduced, but the central casing flexes under inertial forces, causing performance loss
Solution Approach 1:
The patent adds reinforcing structures extending in the longitudinal dimension from the fan casing to the central casing. This longitudinal support prevents the central casing from flexing under inertial forces while maintaining a relatively simple structural configuration that does not require complex radial bracing.
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 configuration enhances the overall performance of the turbojet engine by reducing deformation and elongation, improving the structural integrity and efficiency of the engine assembly.
Implementation Method 1
Each of the first and second front engine mounts is associated with a reinforcing structure forming a shear plane
Data Source
AI summary
An aircraft engine assembly including an annular structure surrounding a central casing and mechanically connected to the central casing by the intermediary of a mounting mechanism. To each of the first and second engine mounts is associated a reinforcing structure forming a shear plane, fixedly connected: in an area of the annular structure at a first anchoring point; in an area of the fan casing at a second anchoring point; and in an area of a structural arm or of the intermediate casing at a third anchoring point. The structure extends along a radial imaginary plane passing through an anchoring point of the mount on the fan casing.