Turbo Compressor Bleed Air Cooling Integration
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Solution Overview
Problem
Gas turbine engines face challenges in efficiently managing bleed air cooling due to increasing operating temperatures, leading to complex and larger heat exchange devices, while maintaining packaging and airframe requirements.
Innovation Solution
A bleed air system that includes a second compressor location within the high-pressure compressor, with valves controlling airflow from the second compressor to the turbine and through the main air passage, allowing for efficient cooling and pressure elevation of bleed air using a turbo compressor.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If heat exchange devices are made larger to cool bleed air at higher temperatures, then cooling efficiency is improved, but device complexity and engine packaging are worsened
Solution Approach 1:
The patent combines the turbo compressor and heat exchange devices into an integrated assembly where the turbine outlet communicates directly with the main air passage downstream of the compressor. This merging eliminates the need for separate, large heat exchange devices by using the turbo compressor's exhaust air flow path as the cooling mechanism, thereby improving cooling efficiency while reducing device complexity and engine packaging requirements.
2Temperature
If heat exchange devices are made larger to cool bleed air at higher temperatures, then cooling efficiency is improved, but engine compactness is worsened
Solution Approach 1:
The patent merges the cooling function into the existing turbo compressor structure by communicating the turbine outlet with the main air passage. This integration allows the system to achieve effective bleed air cooling without adding separate large-volume heat exchange devices, thereby maintaining engine compactness while improving cooling efficiency.
3Temperature
If more cooling air is bled from the compressor section, then turbine cooling is improved, but compressor performance is worsened
Solution Approach 1:
The patent employs self-service by using the turbo compressor's own turbine exhaust air flow to cool the bleed air in the main air passage. Instead of requiring additional compressor output to be bled off for cooling purposes, the system utilizes the turbine's exhaust flow path to provide the cooling function, thereby maintaining compressor performance while achieving effective turbine and bleed air cooling.
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 enhances the efficiency of bleed air cooling, reducing the complexity of heat exchange devices and improving the compactness of gas turbine engines by effectively managing airflow and pressure for aircraft systems.
Implementation Method 1
The high-speed exhaust gas flow expands through the turbine section to drive the compressor and the fan section.
Implementation Method 2
Air entering the compressor section is compressed and delivered into the combustion section
Data Source
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AI summary
A disclosed bleed air system utilizes high pressure air from a high pressure compressor to drive the turbo compressor to increase a pressure of bleed air drawn from the low pressure compressor. Air drawn from the low pressure compressor is at a lower temperature and pressure than that encountered from the high pressure compressor. The turbo compressor increases the pressure of airflow and provides that airflow into the main bleed air passage to be communicated to systems utilizing the bleed air.