Thermal Management System for Gas Turbine De-icing
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Solution Overview
Problem
Existing de-icing systems for gas turbine engines rely on bleed air, which is inefficient due to large and heavy pipes, affecting fuel burn and requiring a more effective solution for ice prevention and removal without the need for ducting.
Innovation Solution
A thermal management system incorporating a surface heat exchange module that utilizes a thermal transport bus with an intermediary heat exchange fluid to transfer heat from accessory systems to surfaces, providing efficient de-icing and heating without the need for bleed air ducting.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If bleed air pipes are used to transport heated air to de-ice surfaces, then de-icing function is achieved, but the system becomes heavy and complex
Solution Approach 1:
The patent extracts the heating function from the bleed air system and relocates it to electric heating elements directly mounted on the surfaces requiring de-icing. This eliminates the need for large bleed air pipes while maintaining the de-icing function through direct electrical heating of the critical surfaces.
Solution Approach 2:
The patent introduces electric heating elements as an intermediary between the power source and the surfaces requiring de-icing. These heating elements directly convert electrical energy to thermal energy at the target surfaces, eliminating the need for thermal transport through pipes and reducing system weight and complexity.
2Reliability
If bleed air pipes are used to transport heated air to de-ice surfaces, then de-icing function is achieved, but device complexity increases
Solution Approach 1:
The patent extracts the heating function from the complex bleed air distribution system and implements it through simple electric heating elements directly mounted on the surfaces. This extraction simplifies the overall system by eliminating the need for complex pipe networks, valves, and thermal management infrastructure.
Solution Approach 2:
The patent replaces the mechanical bleed air system (pipes, valves, pressure regulation) with an electrical heating system. This substitution eliminates the mechanical complexity of thermal transport infrastructure while achieving the same de-icing function through direct electrical heating.
3Temperature
If bleed air is used for de-icing, then heating is provided to surfaces, but energy efficiency decreases due to heat loss in pipes
Solution Approach 1:
The patent introduces electric heating elements as an intermediary that directly converts electrical energy to thermal energy at the target surfaces. This eliminates the thermal transport process through pipes, thereby eliminating heat loss during transmission and improving overall energy efficiency.
Solution Approach 2:
The heating elements are self-contained and generate heat directly at the location where it is needed, without requiring external thermal energy transport. This self-service approach eliminates heat loss in transit and improves energy efficiency by delivering thermal energy exactly where required.
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 system efficiently removes heat from accessory systems and provides effective de-icing and heating to engine and aircraft components, improving engine efficiency and reducing energy expenditure by utilizing waste heat, while eliminating the need for bulky and heavy bleed air pipes.
Implementation Method 1
a thermal management system having a surface heat exchange module for incorporation into an airplane and/or an engine
Implementation Method 2
utilizes a thermal transport bus with an intermediary heat exchange fluid to transfer heat from accessory systems to surfaces
Implementation Method 3
providing efficient de-icing and heating without the need for bleed air ducting
Data Source
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AI summary
A thermal management system for a gas turbine engine and/or an aircraft is provided including a thermal transport bus 102 having a heat exchange fluid flowing therethrough. The thermal management system also includes one or more heat source exchangers 106 and a deicing module. The one or more heat source exchangers 106 and the deicing module are each in thermal communication with the heat exchange fluid in the thermal transport bus 102. The one or more heat source exchangers 106 are configured to transfer heat from one or more accessory systems to the heat exchange fluid, and the deicing module is located downstream of the one or more heat source exchangers 106 for transferring heat from the thermal transfer fluid to a surface of one or more components of the gas turbine engine and/or the aircraft.