Aircraft Bleed Air Turbo-Compressor Extraction
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Solution Overview
Problem
Current bleed air systems in aircrafts face inefficiencies due to high energy wastage when cooling bleed air and the need for large turbo-compressors to achieve sufficient pressure, leading to reduced engine efficiency and increased fuel consumption.
Innovation Solution
A turbo-compressor system that extracts lower-pressure bleed air from a low-pressure compressor stage and boosts its pressure using a turbine, reducing the energy required to produce pressurized air and eliminating the need for a precooler, thereby enhancing fuel efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If bleed air is extracted from a high stage of the low-pressure compressor to meet pressure and temperature demands, then the pressure and temperature requirements are satisfied, but engine efficiency is significantly reduced due to energy wastage in cooling the bleed air
Solution Approach 1:
The patent extracts bleed air from an intermediate stage of the compressor rather than a high stage, taking out the disturbance (high temperature and pressure) earlier in the compression process. This allows the bleed air to be cooled more efficiently with less energy input required, as the temperature differential between the bleed air and cooling medium is reduced.
Solution Approach 2:
The patent changes the extraction point parameter from a high stage to an intermediate stage of the compressor. This parameter change results in bleed air with lower initial temperature and pressure, which requires less energy for cooling while still meeting the required delivery conditions after cooling.
2Use of energy by moving object
If a turbo-compressor is used to pressurize ambient air to supply aircraft systems, then the need for high-pressure bleed air extraction is reduced, but the atmospheric inlet produces drag and is susceptible to icing requiring additional anti-icing systems
Solution Approach 1:
The patent uses the existing compressor infrastructure of the aircraft engine to provide pressurized air, essentially copying the function of a standalone turbo-compressor system but utilizing the already-present compression stages. This eliminates the need for a separate atmospheric inlet and associated anti-icing systems while maintaining energy efficiency.
3Power
If the compressor is made relatively large to produce sufficient pressure change to power aircraft systems, then the pressure requirements are met, but the device size and associated drag increase
Solution Approach 1:
The patent takes out the bleed air requirement from the main compression flow at an intermediate stage, allowing the compressor to be optimized for its primary function of producing thrust while a smaller portion of the compression system handles the bleed air supply. This reduces the overall compressor size needed while maintaining sufficient pressure production capability.
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 significantly reduces energy wastage and fuel consumption by using less energy-intensive bleed air, allowing for a smaller turbo-compressor and minimizing drag, while maintaining sufficient pressure for aircraft systems.
Implementation Method 1
A turbine has a turbine inlet fluidly coupled to the intermediate port of the high-pressure compressor and a high-pressure port of the high pressure compressor
Implementation Method 2
The compressor has a compressor inlet fluidly coupled to a low-pressure compressor of an aircraft engine and an intermediate port of a high-pressure compressor
Data Source
Figure 1A
Figure 1B
Figure 2
AI summary
Bleed air systems for use with aircrafts and related methods are disclosed. An example apparatus includes a turbo-compressor including a compressor has a compressor inlet fluidly coupled to a low-pressure compressor of an aircraft engine and an intermediate port of a high-pressure compressor of the aircraft engine. The compressor inlet to receive fluid from either the low-pressure compressor or the high-pressure compressor based on a first system parameter of the aircraft. A turbine has a turbine inlet fluidly coupled to the intermediate port of the high pressure compressor and a high-pressure port of the high pressure compressor of the aircraft engine. The turbine inlet to receive fluid from either the intermediate port of the high-pressure compressor or the high-pressure port of the high-pressure compressor based on a second system parameter of the aircraft.