Integrated Engine Bleed Air Routing for Multi-Pressure Distribution
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Solution Overview
Problem
Aircraft systems that require pressurized air often have dedicated bleed lines for high-pressure and low-pressure air, leading to complex plumbing and increased weight, with some systems needing heat exchangers to condition high-pressure air, resulting in inefficiencies.
Innovation Solution
An integrated turbine engine bleed system that combines low-pressure and high-pressure air sources into a single system, using shut-off valves and heat exchangers to distribute air to multiple aircraft sub-systems, regulated by a controller to optimize pressure and temperature based on demand.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If dedicated bleed lines are used for each system requiring pressurized air, then each system receives reliable pressurized air supply, but plumbing complexity and system weight increase
Solution Approach 1:
The patent combines multiple dedicated bleed lines into a single integrated bleed system that serves multiple aircraft systems. The integrated system includes a common bleed air manifold that distributes pressurized air to various systems (air conditioning, pressurization, anti-icing) through selective valves, eliminating the need for separate bleed lines for each system while maintaining reliable supply to all.
Solution Approach 2:
The integrated bleed system is designed as a universal supply system that can serve multiple different aircraft systems simultaneously. The common manifold and selective valve arrangement allow the single bleed system to provide pressurized air to different systems on demand, making the system multi-functional rather than dedicated to a single purpose.
2Reliability
If multiple individual bleed lines are used for different systems, then each system has dedicated pressurized air supply, but system weight increases
Solution Approach 1:
The patent merges multiple separate bleed lines into a single integrated bleed system with a common manifold. This consolidation reduces the total amount of plumbing required and thereby reduces system weight, while the selective valve arrangement ensures that each system still receives dedicated pressurized air supply when needed.
3Temperature
If heat exchangers are added to condition high-pressure air for each system, then air temperature is properly conditioned, but device complexity and weight increase
Solution Approach 1:
The patent consolidates multiple heat exchanger systems into a single integrated heat exchanger unit that conditions air for the entire bleed system. The heat exchanger is positioned in the common bleed air manifold, allowing it to condition air before distribution to multiple systems, thereby reducing the total number of heat exchangers needed while maintaining proper temperature conditioning.
Solution Approach 2:
The integrated heat exchanger serves as a universal conditioning device for the entire bleed system rather than having separate heat exchangers for each system. This multi-functional heat exchanger conditions air for multiple systems simultaneously, reducing overall system complexity while maintaining proper temperature control for each downstream system.
4Stress or pressure
If separate bleed lines are used for high-pressure and low-pressure air, then pressure requirements are met, but plumbing complexity increases
Solution Approach 1:
The patent combines high-pressure and low-pressure bleed lines into a single integrated system with a common manifold. Pressure regulation valves are installed at the manifold to control and distribute air at appropriate pressures to different systems, eliminating the need for completely separate high-pressure and low-pressure plumbing while still meeting all pressure requirements.
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
Reduces plumbing complexity and weight by consolidating air sources, optimizing pressure and temperature distribution, and enhancing system efficiency without the need for multiple pressure taps or individual feeds.
Implementation Method 1
a heat exchanger that employs the low-pressure air as a cooling medium to condition the high-pressure air
Data Source
AI summary
A turbine engine for an aircraft includes a compressor with a low-pressure spool including a low-pressure tap and a high-pressure spool including a high-pressure tap and a combustor connected to the compressor. The engine includes a turbine connected to the combustor and that includes an inlet section connected to the outlet portion of the combustor and an outlet section. The engine also includes an integrated engine bleed system connected to the compressor and a plurality of aircraft sub-systems. The integrated engine bleed system connects the high/low pressure taps various aircraft sub-systems.