Aft-Mounted Electric Machine Cooling in Reverse-Flow Turbines
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Solution Overview
Problem
Existing gas turbine engines with reverse flow configurations face challenges in integrating auxiliary components like electric machines efficiently, particularly in terms of heat management and packaging, due to their proximity to heat-generating sections.
Innovation Solution
The electric machine is positioned aft of the core turbine engine and coupled to the low-pressure shaft, allowing for heat exchange with the intake air flow through a non-annular to annular intake channel design, enabling effective cooling and tighter packaging.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Volume of moving object
If the electric machine is positioned near the heat-generating sections of the gas turbine engine, then compact integration is achieved, but thermal stress and heat management challenges increase
Solution Approach 1:
The electric machine is extracted from the traditional forward position and relocated to the aft section of the gas turbine engine, separating it from heat-generating components such as the compressor and combustion chamber. This spatial extraction reduces thermal stress while maintaining compact integration through optimized aft-section packaging.
Solution Approach 2:
The electric machine is positioned in the aft dimension of the engine, utilizing previously underutilized space behind the turbine. This dimensional relocation allows compact integration in the aft direction while naturally distancing the electric machine from forward heat sources, thereby reducing thermal stress.
2Object-affected harmful factors
If the electric machine is positioned aft of the core turbine engine, then thermal stress is minimized, but packaging efficiency and heat exchange capability are reduced
Solution Approach 1:
The electric machine is positioned in the aft dimension of the engine, utilizing previously underutilized space behind the turbine. This dimensional relocation allows compact integration in the aft direction while naturally distancing the electric machine from forward heat sources, thereby reducing thermal stress.
Solution Approach 2:
A cooling air flow path acts as an intermediary between the intake channel and the electric machine, enabling effective heat exchange while maintaining the aft positioning. The cooling air serves as a thermal mediator that facilitates heat removal from the electric machine without requiring direct proximity to heat-generating sections.
3Object-affected harmful factors
If the electric machine is positioned aft of the core turbine engine, then heat management is improved, but integration complexity increases
Solution Approach 1:
The aft section of the engine is designed to serve multiple functions: housing the electric machine, providing cooling air flow paths, and managing thermal loads. This multi-functionality approach consolidates heat management and integration tasks into a unified aft-section design, reducing overall system complexity despite the relocated positioning.
Solution Approach 2:
The cooling air flow path is configured to automatically route cooling air from the intake channel to the electric machine in the aft section. This self-service cooling system operates without additional active control mechanisms, simplifying the integration of heat management functions while maintaining effective thermal control.
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 allows for efficient heat management and compact integration of the electric machine, enhancing power supplementation and thrust capabilities while minimizing thermal stress.
Implementation Method 1
the electric machine transfers heat to the incoming flow of air within the intake channel
Implementation Method 2
the intake channel configured to turn the received incoming flow of air from an incoming flow direction to an axial direction of the gas turbine engine
Data Source
AI summary
An aircraft engine assembly includes a gas turbine engine having an intake channel configured to receive an incoming flow of air and form an intake flow of air, the intake channel configured to turn the received incoming flow of air from an incoming flow direction to a first axial direction of the gas turbine engine, the incoming flow direction reverse of the first axial direction, and an electric machine coupled with the low pressure shaft and located at the aft end of the gas turbine engine proximate the intake channel, the electric machine in heat exchange communication with the intake flow of air such that the electric machine transfers heat to the incoming flow of air within the intake channel when the electric machine is operated.