Gas Turbine Engine Thermal Management System
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Solution Overview
Problem
Gas turbine engines experience power loss due to heat rejection in APU exhaust gases during ground operation and transitional flight stages, and motor-actuated flight control surfaces generate power that is lost as heat, leading to inefficiencies and reduced performance.
Innovation Solution
A gas turbine engine with an integrated Thermal Management System (TMS) and Environmental Control System (ECS) powered by the low spool, which includes a TMS pump and ECS pump driven by the low spool to manage thermal energy and recover thrust, and an algorithm to accelerate the low spool using excess power during transient conditions, thereby maintaining efficiency and reducing heat loss.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If APU is used for power generation during ground operation and transitional stages, then excess power is produced, but power is lost as heat in exhaust gases
Solution Approach 1:
The patent captures the harmful hot exhaust gases from the APU and redirects them through a heat exchanger to generate useful thermal energy for cabin heating and thermal management, converting the waste heat into a beneficial resource that eliminates the energy loss
Solution Approach 2:
The system recovers thermal energy from the exhaust gases that would otherwise be discarded, using a heat exchanger to extract heat from the exhaust stream and utilize it for aircraft thermal management needs, thereby preventing energy waste
2Ease of operation
If motor-actuated flight control surfaces are used, then flight control is achieved, but power is lost as heat to atmosphere
Solution Approach 1:
The patent captures the waste heat generated by motor-actuated flight control surfaces and redirects it through heat exchangers to contribute to cabin heating and thermal management, converting the previously lost energy into a useful thermal resource
3Productivity
If low spool is accelerated using excess power during transient conditions, then operational efficiency is maintained, but system complexity increases
Solution Approach 1:
The patent implements a control system with sensors that monitor engine parameters (N1 speed, EGT, thrust demand) and provide feedback to the controller, which automatically adjusts fuel flow and air intake to accelerate the low spool during transient conditions, maintaining efficiency without requiring complex manual intervention
Solution Approach 2:
The system uses the engine's own excess power to accelerate the low spool during transient conditions through automated control, eliminating the need for external assistance or complex additional systems, as the engine self-regulates to maintain optimal performance
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 solution effectively recovers thermal energy, reduces exhaust gas temperature, decreases system weight, and increases operational range while minimizing mechanical complexity and packaging volume, enhancing reliability and reducing maintenance costs.
Implementation Method 1
A gas turbine engine with an integrated Thermal Management System (TMS) and Environmental Control System (ECS) powered by the low spool, which includes a TMS pump and ECS pump driven by the low spool to manage thermal energy and recover thrust
Data Source
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AI summary
A gas turbine engine includes an Integrated Drive Generator (IDG) (130) geared to a low spool (30) to selectively accelerate the low spool (30) during a transient condition.