Active Bleed Air Cooling Control for Gas Turbine Efficiency
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Conventional cooling methods in gas turbine engines require large amounts of airflow to effectively reduce component temperatures in high-pressure areas, as the high operating temperatures exceed material limits and necessitate improved cooling air delivery.
Innovation Solution
A bleed air cooling system that diverts high-pressure compressor airflow into a bleed duct, where it is modulated by sensors and a control system to optimize airflow distribution to the turbine section through a network of bleed manifolds and valves, ensuring efficient cooling of components.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If large amounts of airflow are used for cooling turbine components, then component temperatures are reduced below material limits, but engine efficiency decreases and excessive cooling air is consumed
Solution Approach 1:
The system dynamically adjusts cooling airflow parameters (flow rate, distribution) based on real-time operating conditions such as turbine temperature sensors, engine speed, and load. This allows optimization of cooling efficiency to minimize energy loss while maintaining component temperatures within safe limits.
Solution Approach 2:
The patent implements active control systems with sensors and actuators that continuously monitor and adjust cooling airflow in real-time. This dynamic adaptation enables the system to provide precise cooling only when and where needed, reducing excessive cooling air consumption and improving overall engine efficiency.
2Temperature
If high-pressure compressor air is diverted for cooling, then turbine section cooling is improved, but compressor discharge pressure is reduced
Solution Approach 1:
The system extracts bleed air from specific locations within the compressor section and delivers it to specific cooling requirements in the turbine section. This localized approach ensures cooling is provided precisely where heat dissipation is most critical, optimizing the balance between cooling effectiveness and pressure maintenance.
Solution Approach 2:
Cooling air is bled off from the compressor at predetermined stages where pressure and temperature conditions are optimal. This preliminary extraction of cooling air before final compression allows the system to maintain adequate discharge pressure while still providing sufficient cooling airflow to the turbine section.
3Temperature
If conventional cooling air methods are used, then component cooling is provided, but large amounts of cooling air are required to achieve sufficient pressure and temperature reduction
Solution Approach 1:
The system incorporates temperature sensors in the turbine section that provide feedback to the control system. Based on this feedback, the control system adjusts the amount of cooling airflow from the compressor to match actual cooling requirements, minimizing the quantity of cooling air needed while maintaining component temperatures within safe operating limits.
Solution Approach 2:
Instead of providing excessive cooling air to all turbine components uniformly, the system applies partial cooling action only to the specific components and locations that require it most, based on thermal mapping and operational requirements. This targeted approach reduces overall cooling air quantity while maintaining effective cooling where critical.
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 approach allows for adaptable and efficient cooling of turbine components by optimizing airflow based on real-time operating conditions, enhancing the engine's thermal management and operational efficiency.
Implementation Method 1
cooling air is often provided from the compressor to the turbine section to reduce component temperature in the turbine section
Data Source
Figure 1
Figure 2
Figure 3
AI summary
A bleed air cooling system (72) for a gas turbine engine includes a bleed port (58; 58a, 58b) located at an axial location of the gas turbine engine to divert a bleed airflow (66; 66a, 66b) from a gas turbine engine flowpath, a bleed outlet located at a cooling location of the gas turbine engine and a bleed duct (60; 60a, 60b) in fluid communication with the bleed port (58; 58a, 58b) and configured to convey the bleed airflow (66; 66a, 66b) from the bleed port (58; 58a, 58b) to the bleed outlet. A modulating valve (74; 74a, 74b) is located at the bleed duct (60; 60a, 60b) and is movable between a fully open position and a fully closed position to regulate the bleed airflow (66; 66a, 66b) through the bleed duct (60; 60a, 60b) based on one or more operating conditions of the gas turbine engine.