Aircraft Air Management System Single Port Electrical Compressor
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Solution Overview
Problem
Conventional air management systems in aircraft face inefficiencies due to reliance on dual bleed ports, leading to energy loss and spurious leakage detection issues, especially with the advent of Ultra-High By-Pass Ratio engines, which require optimized energy extraction from gas turbine engines.
Innovation Solution
An air management system utilizing a single port at a low-intermediate compressor stage and an electrical compressor to selectively supply compressed air based on aircraft operation conditions, eliminating the need for a high-pressure port and associated ducting, and using electrical compressors to offset energy peaks during demanding flight phases.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If a dual bleed port system (IP and HP ports) is used to supply compressed air to air consumers, then the system can operate across a wide range of flight conditions, but the system experiences significant energy loss during take-off/climb and descent/holding phases
Solution Approach 1:
The air management system is segmented into multiple independent air sources: an intermediate pressure bleed system and a high pressure bleed system, each optimized for specific flight phases. The control system selectively activates appropriate sources based on flight conditions, avoiding the energy inefficiency of using a single oversized system across all phases.
Solution Approach 2:
The system dynamically switches between different air sources (IP port, HP port, electrical compressors) based on real-time flight parameters such as altitude, speed, and phase of flight. This dynamic adaptation allows the system to optimize energy consumption by using the most efficient air source for each specific operational condition.
2Productivity
If the air management system is sized to operate at any planned flight phase, then all flight conditions are covered, but the system experiences significant energy loss during non-cruise phases
Solution Approach 1:
The patent replaces the traditional mechanical bleed air system with electrical compressors for certain flight phases. Electrical compressors can be more energy-efficient than bleeding air from engine compressors during ground operations, take-off, and descent, thereby reducing overall energy consumption while maintaining system availability.
Solution Approach 2:
The system changes operational parameters by switching between different air pressure sources and temperature conditions based on flight phase. During cruise, the system operates in a optimized state using bleed air from the IP port, while during other phases it transitions to alternative sources, effectively managing energy consumption across varying operational parameters.
3Power
If bleed air is extracted at high pressure and temperature from the engine, then air consumer equipment can be operated, but the channeling means must withstand high temperature and pressure requiring robust design
Solution Approach 1:
The air management system is divided into separate high-pressure and intermediate-pressure ducting networks. By segmenting the system, each ducting network can be optimized for its specific pressure and temperature range, reducing the overall complexity compared to a single robust system designed for maximum conditions.
Solution Approach 2:
The patent introduces intermediate pressure ports and pressure reduction stages as mediators between the high-pressure engine compressor and the air consumer equipment. These intermediaries allow the system to deliver high power when needed while protecting downstream components from excessive pressure and temperature, simplifying the overall ducting requirements.
4Reliability
If eutectic salt-based sensors are installed for bleed air leakage detection, then leakage can be detected, but aircraft vibration may induce rattling causing spurious alerts and unnecessary isolation
Solution Approach 1:
The system uses feedback from multiple sensors and control parameters to verify leakage conditions. By monitoring temperature, pressure, and flow rate simultaneously, the system can distinguish between actual leaks and false alerts caused by vibration, improving operational reliability while reducing unnecessary isolations.
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 solution reduces energy consumption by 1% Thrust-specific fuel consumption, enhances operational safety, and simplifies the system by eliminating high-pressure ducting and associated equipment, while optimizing air distribution during cruise phases.
Implementation Method 1
at least one electrical compressor in fluid communication with the air source, the at least one electrical compressor being configured to supply compressed air to the at least one air consumer
Implementation Method 2
air is normally taken from compressor stages upstream of the fuel-burning chamber(s) of gas turbine engines. Thus, this bleed air is at high temperature and high pressure
Implementation Method 3
after regulation in a pre-cooler
Data Source
Figure 1
Figure 2a~2b
Figure 3a
AI summary
The present invention provides an air management system with a set of compressed air sources for supplying pressurized air to air consumer equipment. In particular, either an air bleed system, electrical compressors, or a combination thereof may perform such supplying of compressed air depending on the aircraft operation condition.