Modulating Bleed Air Cooling for Gas Turbine Temperature Control
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Solution Overview
Problem
Conventional cooling methods in gas turbine engines require large amounts of airflow to manage high temperatures, exceeding material limits, necessitating improved cooling air systems.
Innovation Solution
A bleed air cooling system with a modulating valve in a bleed duct that regulates airflow based on engine operating conditions, using sensors and a control system to optimize cooling airflow to turbine components.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If large amounts of airflow are used for cooling turbine components, then component temperature is reduced, but airflow consumption increases excessively
Solution Approach 1:
The patent implements a modulating valve that dynamically adjusts the bleed air flow rate based on real-time turbine component temperature measurements. The valve transitions from static full-open or closed positions to continuous modulation capability, allowing the system to provide exactly the amount of cooling airflow needed at any given moment, thereby reducing excessive airflow consumption while maintaining temperature control.
Solution Approach 2:
The patent incorporates temperature sensors that continuously monitor turbine component temperatures and feed this information back to the control system. This feedback loop enables the modulating valve to adjust bleed air flow rates responsively, ensuring optimal cooling efficiency without requiring large fixed airflow quantities, thus resolving the contradiction between temperature control and airflow consumption.
2Use of energy by moving object
If high temperatures are maintained in the turbine section, then efficiency gains are achieved, but material limits are exceeded
Solution Approach 1:
The patent enables the turbine cooling system to self-regulate by using temperature sensors mounted directly on turbine components to detect actual component temperatures. This self-service approach allows the system to automatically adjust bleed air flow rates to maintain temperatures within material limits while maximizing efficiency, eliminating the need for conservative fixed cooling rates that would reduce overall engine efficiency.
3Temperature
If conventional cooling air methods are used, then cooling is provided, but large amounts of airflow are required to achieve sufficient cooling at high pressure locations
Solution Approach 1:
The patent changes the flow rate parameter of bleed air dynamically through modulating valve control. By adjusting the flow rate parameter in response to temperature sensor feedback, the system achieves effective cooling at high pressure locations with variable airflow quantities rather than requiring consistently large airflow volumes, thus resolving the contradiction between cooling effectiveness and airflow volume 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
Enhances cooling efficiency by adaptively managing airflow, reducing the need for excessive airflow while maintaining component temperature within material limits.
Implementation Method 1
air from the high compressor discharge is passed through a heat exchanger, which may be located in a fan bypass duct and then delivered into the turbine section as cooling air
Data Source
AI summary
A bleed air cooling system for a gas turbine engine includes a bleed port located at an axial location of the gas turbine engine to divert a bleed airflow from a gas turbine engine flowpath, a bleed outlet located at a cooling location of the gas turbine engine and a bleed duct in fluid communication with the bleed port and the configured to convey the bleed airflow from the bleed port to the bleed outlet. A modulating valve is located at the bleed duct and is movable between a fully open position and a fully closed position to regulate the bleed airflow through the bleed duct based on one or more operating conditions of the gas turbine engine.