Aircraft Energy Management System Fan Discharge Air Compressor
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Solution Overview
Problem
Conventional aircraft environmental control systems (ECS) face challenges in reducing aircraft weight and minimizing drag penalties, particularly when using composite materials and electrically powered anti-ice systems, as they require high-temperature bleed air and additional power sources, leading to increased weight and drag.
Innovation Solution
An aircraft energy management system that extracts fan discharge air from a turbine engine, compresses it, and directs it to an environmental control system, minimizing weight and drag by utilizing the fan pressure ratio and reducing ram air drag losses, with a cabin air compressor mechanically coupled to the engine and an environmental control system configured to operate in both flight and ground modes.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If conventional ECS uses engine bleed air for composite aircraft, then high temperature anti-icing is achieved, but aircraft weight increases and composite material temperature limits are exceeded
Solution Approach 1:
The system segments the air supply function by providing separate low-temperature air sources for cooling and high-temperature air sources for anti-icing, allowing independent control of temperature for different functions while avoiding overheating of composite materials
Solution Approach 2:
The system changes the temperature parameter of air supplied to different zones: low-temperature air (below 93°C) for composite structures and high-temperature air for metal anti-icing surfaces, matching temperature to material requirements
2Temperature
If electrically driven ECS is used in composite aircraft, then low-temperature air supply is achieved, but electrical power requirements increase generator size
Solution Approach 1:
The engine bleed air system serves multiple functions: it provides both low-temperature air for cooling composite structures and high-temperature air for anti-icing, eliminating the need for separate electrically-driven systems and their associated power requirements
Solution Approach 2:
The system uses the engine's own bleed air to satisfy both cooling and anti-icing requirements, making the system self-sufficient without requiring external electrical power sources or additional generators
3Quantity of substance
If additional air intakes are added for electrically driven ECS, then ambient air entrainment is improved, but aircraft drag increases
Solution Approach 1:
The engine intake serves dual purposes: it supplies air for both the cooling system and the anti-icing system, eliminating the need for additional dedicated air intakes and the associated drag penalties
4Temperature
If conventional ECS interface is used with composite aircraft, then high-temperature bleed air is provided, but precooler size must be significantly increased
Solution Approach 1:
The system segments air supply by temperature requirements, providing separate low-temperature air paths for composite structures, which eliminates or significantly reduces the size of precooolers needed for composite air supplies
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 effectively provides conditioned airflow to the aircraft cabin while reducing overall aircraft weight and minimizing drag, achieving efficient energy management and fuel savings by leveraging the fan pressure ratio and using a low-pressure, low-temperature interface compatible with composite materials.
Implementation Method 1
compressing it, and directs it to an environmental control system
Implementation Method 2
cooled by a heat exchanger
Data Source
AI summary
An aircraft energy management system including a cabin air compressor adapted to be coupled to a source of fan discharge air at a first pressure during an inflight operating mode and adapted to be coupled to a ram intake air during a ground operating mode. The system further including an environmental control system mechanically coupled to a compressor exit of the cabin air compressor. The aircraft energy management system configured to provide a conditioned fluid flow to an aircraft cabin, cockpit or de-icing system.