Triple-Flow Aircraft Turbine Suspension With Cold-Compartment Mounting
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Solution Overview
Problem
Existing turbine engine designs face challenges in thermal management and suspension configuration, leading to reduced equipment service life, increased mass, and maintenance complexity due to thermal protection volumes and limited space for sensitive equipment.
Innovation Solution
The turbine engine design relocates suspension members to the cold compartment, utilizing a structural third wall for force transmission, eliminating downstream suspension members and thrust-absorbing rods, and optimizing the cold compartment for equipment installation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If suspension members are located in the hot compartment, then thermal protection volumes are required, but this increases mass and reduces equipment service life
Solution Approach 1:
The patent extracts sensitive equipment from the hot compartment and relocates them to the cold compartment. This eliminates the need for thermal protection volumes around equipment, thereby reducing the overall mass of the turbine engine while maintaining thermal protection for components that remain in the hot compartment.
Solution Approach 2:
The patent utilizes the spatial dimension by creating distinct hot and cold compartments within the engine structure. By positioning suspension members and sensitive equipment in the cold compartment (a different thermal dimension), the design avoids the mass penalty of thermal protection without compromising the thermal environment of the hot compartment.
2Object-affected harmful factors
If thermal protection volumes are added for equipment in hot compartment, then equipment service life is reduced, but this provides thermal protection
Solution Approach 1:
The patent extracts sensitive equipment from the hot compartment environment and places them in the cold compartment. This extraction eliminates the harmful thermal effects that would reduce equipment service life, while the hot compartment retains its thermal protection for components designed to operate in high-temperature environments.
Solution Approach 2:
The patent applies different thermal qualities to different compartments: the hot compartment maintains high temperature for thermal management and propulsion efficiency, while the cold compartment provides a thermally stable, protected environment for sensitive equipment, thereby extending their service life.
3Strength
If downstream suspension members and thrust-absorbing rods are retained, then structural support is provided, but this increases device complexity
Solution Approach 1:
The patent merges the functions of downstream suspension members and thrust-absorbing rods into an integrated upstream suspension member configuration. This consolidation maintains the necessary structural support and strength while eliminating redundant components, thereby reducing device complexity.
Solution Approach 2:
The upstream suspension members are designed to perform multiple functions: they provide structural support, absorb thrust forces, and serve as mounting points for equipment. This multi-functionality eliminates the need for separate downstream suspension members and thrust-absorbing rods, simplifying the overall suspension configuration.
4Ease of repair
If cold compartment space is optimized for equipment installation, then accessibility and maintenance are improved, but this requires reconfiguring suspension members
Solution Approach 1:
The patent extracts equipment from the hot compartment and relocates them to the cold compartment, which is designed with improved accessibility features. This extraction enables better maintenance access while the simplified upstream suspension configuration reduces overall device complexity.
Solution Approach 2:
The patent creates a dedicated cold compartment dimension that is spatially separated from the hot compartment. This dimensional separation allows equipment to be installed in an accessible location within the cold compartment while maintaining the structural integrity and simplified configuration of the upstream suspension members.
Data Source
AI summary
A triple-flow turbine engine for an aircraft, this turbine engine having a longitudinal axis and including upstream suspension elements which are located in a first plane perpendicular to the axis and are connected or fixed to the gas generator of the turbine engine; downstream suspension elements which are located in a second plane perpendicular to the axis and are connected or fixed to the gas generator; and thrust-absorbing rods which include first ends which are connected or fixed to the gas generator and opposing second ends which are located in a third plane perpendicular to the axis, wherein the first, second and third planes are located at a cold compartment of the gas generator.