Aircraft Propulsion Thermal Assembly With Split Cooling Loops
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Solution Overview
Problem
Existing thermal management systems for aircraft propulsion systems, particularly those involving motor-generators and motor control units, face challenges in efficiently managing the varying temperature extremes and operational conditions, with motor-generators and motor control units having different temperature control requirements, complicating effective thermal management.
Innovation Solution
A thermal management assembly is implemented with independent cooling systems for motor-generators and motor control units, utilizing separate heat exchangers and coolant types to optimize temperature control, reducing the need for shared components and fluid interconnections, and minimizing weight and drag losses.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If separate cooling systems are used for motor-generators and motor control units, then temperature control precision is improved, but device complexity increases
Solution Approach 1:
The cooling system is divided into separate independent loops for motor-generators and motor control units, allowing each component to be cooled according to its specific thermal requirements without interference from the other
Solution Approach 2:
The bypass duct structure serves multiple functions: it provides aerodynamic flow path, houses heat exchangers for both cooling systems, and integrates with the bifurcations to distribute coolant, eliminating the need for separate dedicated cooling structures
2Temperature
If independent cooling systems with separate heat exchangers are implemented, then temperature control for different components is optimized, but weight increases
Solution Approach 1:
The heat exchangers for motor-generators and motor control units are combined within the same bypass duct structure, sharing common structural support, mounting interfaces, and aerodynamic housing, thereby reducing redundant materials and overall weight
Solution Approach 2:
The heat exchanger assemblies are nested within the bypass duct structure, with one heat exchanger positioned inside or adjacent to another, utilizing the available space efficiently and eliminating the need for separate external cooling components
3Temperature
If separate cooling systems are used for motor-generators and motor control units, then temperature control precision is improved, but drag losses increase
Solution Approach 1:
The bypass duct structure serves multiple functions: it provides aerodynamic flow path, houses heat exchangers for both cooling systems, and integrates with the bifurcations to distribute coolant, eliminating the need for separate dedicated cooling structures
Solution Approach 2:
The heat exchangers are positioned within the bypass duct in a configuration that utilizes the three-dimensional space efficiently, arranging components to minimize disruption to the aerodynamic flow while maintaining effective heat transfer surfaces
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
The independent cooling systems provide improved temperature control for motor-generators and motor control units, reducing cooling needs and weight while maintaining optimal operating conditions, and facilitating reduced drag and increased efficiency in thermal management.
Implementation Method 1
The MG cooling system includes a first heat exchanger disposed at the first bifurcation within the annular bypass duct. The MCU cooling system includes a second heat exchanger disposed at the second bifurcation within the annular bypass duct.
Implementation Method 2
The nacelle body forms an annular bypass duct between the nacelle body and the inner fixed structure. The first heat exchanger is disposed at the first bifurcation within the annular bypass duct. The second heat exchanger is disposed at the second bifurcation within the annular bypass duct.
Data Source
AI summary
An aircraft propulsion system includes a gas turbine engine, a nacelle, and an electrical assembly. The gas turbine engine includes a rotational assembly and an inner fixed structure. The nacelle includes a nacelle body, a first bifurcation, and a second bifurcation. The nacelle body extends circumferentially about the gas turbine engine. The nacelle body forms an annular bypass duct between the nacelle body and the inner fixed structure. The first bifurcation and the second bifurcation extend between and connect the nacelle body and the inner fixed structure. The electrical assembly includes a motor-generator, a motor control unit, a motor-generator (MG) cooling system, and a motor control unit (MCU) cooling system. The motor-generator is coupled to the shaft. The motor control unit is electrically connected to the motor-generator. The MG cooling system includes a first heat exchanger disposed at the first bifurcation. The MCU cooling system includes a second heat exchanger disposed at the second bifurcation.