Multi-Flow Turbine Engine Layout for Cold Compartment Cooling
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Solution Overview
Problem
Existing turbine engine designs face challenges in thermal management during low engine speed phases, leading to inadequate cooling of equipment, increased mass and complexity due to bulky thermal protections, and limited space for heat-sensitive components.
Innovation Solution
Optimizing the geometrical characteristics of the turbine engine by increasing the volume and diameter of the cold compartment relative to the hot compartment, with specific radius and volume ratios, and protecting it with the duct for the secondary flux to enhance thermal insulation and equipment integration.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If the bypass ratio is increased to improve engine performance, then thrust increases and fuel consumption decreases, but the mass of the turbine engine increases due to the larger propeller diameter required
Solution Approach 1:
The invention segments the turbine engine into distinct hot and cold compartments with separate functional zones. The cold compartment is dedicated to thermal management and housing heat-sensitive equipment, while the hot compartment handles combustion and high-temperature operations. This segmentation allows optimized space utilization without requiring excessive overall engine size.
Solution Approach 2:
The invention utilizes the radial dimension by creating a cold compartment that extends radially outward between the combustion chamber and the propeller intake. This radial expansion allows additional volume for thermal management equipment without significantly increasing the axial length or overall engine diameter, thus avoiding direct proportionality between bypass ratio and engine mass.
2Reliability
If thermal protections are added to protect equipment in the hot compartment, then equipment reliability improves, but the device complexity and mass increase due to bulky thermal protections
Solution Approach 1:
The invention extracts heat-sensitive equipment from the hot compartment environment and places it in the cold compartment. By separating thermally sensitive components from the high-temperature zone, extensive thermal protections are eliminated or reduced to minimal shielding, thereby reducing device complexity and mass while maintaining equipment reliability.
Solution Approach 2:
The cold compartment acts as an intermediary thermal zone between the hot combustion chamber and the equipment requiring cooling. This intermediary space provides thermal buffering and allows equipment to operate in a controlled temperature environment without requiring heavy thermal protection systems.
3Temperature
If the secondary flux flow rate is increased to improve thermal management, then equipment cooling improves, but the flow rate becomes insufficient during low engine speed phases
Solution Approach 1:
The cold compartment is pre-configured with dedicated cooling ducts and thermal management equipment that can operate independently of the secondary flux flow rate. This preliminary arrangement of cooling infrastructure ensures that thermal management capability is built into the engine structure, allowing it to function effectively even when secondary flux flow is reduced at low engine speeds.
Solution Approach 2:
The cold compartment serves multiple functions: it provides thermal management for equipment, houses heat-sensitive components, and acts as a buffer zone. This multi-functionality ensures that thermal management is not solely dependent on secondary flux flow rate, as the compartment's structural design and integrated cooling systems can maintain equipment cooling across various engine operating conditions.
4Adaptability or versatility
If the volume of the cold compartment is increased to accommodate more equipment, then equipment integration improves, but the space in the hot compartment is reduced
Solution Approach 1:
The cold compartment expands radially outward in the space between the combustion chamber and propeller intake, utilizing the radial dimension rather than consuming axial or longitudinal space. This dimensional strategy allows the cold compartment volume to be increased for better equipment integration without encroaching on the hot compartment volume, as the two compartments are radially separated rather than competing for the same spatial envelope.
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
Facilitates the integration of more equipment, particularly heat-sensitive components, while improving thermal protection and reducing maintenance complexity, thus enhancing engine performance and extending equipment lifespan.
Implementation Method 1
protected in the event of a fire by the duct for the flow of the second external flux F12, which also protects the cold compartment from thermal radiation linked to combustion
Implementation Method 2
protecting it with the duct for the secondary flux to enhance thermal insulation
Implementation Method 3
an additional bypass flux that is dedicated to the thermal management of the turbine engine
Implementation Method 4
the flow rate of the secondary flux F2 generated is sufficient to feed fluid/air exchangers 26
Data Source
AI summary
A multi-flow turbine engine for an aircraft, the turbine engine having a gas generator with geometrical characteristics allowing it to have at its periphery a cold compartment larger than its hot compartment.