Variable Turbine Cooling Flow Control for Gas Turbine Efficiency
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Solution Overview
Problem
Gas turbine engines face inefficiencies due to the need for active cooling in high-temperature regions, which affects performance and fuel efficiency, and are typically designed under worst-case, highest-temperature conditions.
Innovation Solution
A gas turbine engine with a compressor section, combustor section, and turbine section, featuring a primary flow path and an engine case, incorporates a means for providing an active variable cooling flow through a bypass duct external to the engine case to a secondary flow cavity of the turbine section, controlled by a cooling air metering valve that can be electronically actuated based on flight phase and operating parameters.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If active cooling is provided to high-temperature regions in the turbine section, then the reliability and durability of turbine parts are improved, but the engine efficiency deteriorates due to cooling air branches losing work without imparting motive force
Solution Approach 1:
The patent implements variable cooling flow control that dynamically adjusts the amount of cooling air supplied to turbine parts based on operating conditions. The cooling system transitions from a static fixed-flow design to a dynamic variable-flow design, allowing the engine to optimize between cooling needs and efficiency requirements across different flight phases and operating parameters.
Solution Approach 2:
The patent changes the parameter of cooling air flow rate from a fixed value to a variable parameter that can be adjusted based on operating conditions. By implementing electronic control that modifies the cooling air flow parameter in response to flight phase and engine operating parameters, the system resolves the contradiction between maintaining adequate cooling and preserving engine efficiency.
2Reliability
If turbine parts are designed for worst-case highest-temperature conditions, then the reliability under extreme conditions is improved, but the engine performance deteriorates due to excessive cooling requirements
Solution Approach 1:
The patent implements a dynamic cooling control system that adjusts cooling flow based on actual operating conditions rather than designing for static worst-case conditions. The system monitors flight phase and engine operating parameters to dynamically modulate cooling air supply, ensuring adequate cooling when needed while minimizing excessive cooling during normal operations, thereby improving overall engine performance.
Solution Approach 2:
The patent applies partial cooling action rather than continuous maximum cooling. By providing cooling air only when and where needed based on actual thermal conditions and operating parameters, the system avoids the excessive cooling that would be required if designed for worst-case conditions at all times, thus improving engine performance without compromising reliability.
3Ease of manufacture
If fixed cooling flow is provided to turbine sections, then the manufacturing and design simplicity is maintained, but the adaptability to different flight phases and operating conditions deteriorates
Solution Approach 1:
The patent implements a universal cooling control system that handles multiple flight phases and operating conditions through a single integrated electronic control architecture. The control system universally manages cooling air flow across takeoff, climb, cruise, descent, and ground operations, replacing multiple fixed-flow designs with one adaptive system that provides optimal cooling for all operating conditions.
Solution Approach 2:
The patent transforms the static cooling system into a dynamic one capable of adapting to different flight phases and operating conditions. The electronic control system continuously monitors engine parameters and adjusts cooling air flow accordingly, providing the adaptability needed for versatile operation while maintaining reasonable design complexity through systematic control architecture.
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 enables dynamic adjustment of cooling flow to optimize turbine section cooling, improving engine efficiency and reducing fuel consumption by tailoring cooling to specific flight phases and operating conditions.
Implementation Method 1
A cooling air metering valve can be provided that is electronically actuated based on either or both of a flight phase and an operating parameter of the gas turbine engine
Implementation Method 2
A bypass duct can be provided that extends external to the engine case around the combustor section from the compressor bleed port to at least one static support structure cooling supply cavity of the turbine section
Implementation Method 3
The airflow path includes an inner diffuser flow path configured to deliver a metered supply of cooling air from the compressor section through a diffuser section proximate to the combustor section
Data Source
AI summary
A gas turbine engine includes a compressor section, a combustor section, and a turbine section operably coupled to the compressor section. A primary flow path is defined through the compressor section, the combustor section, and the turbine section. An engine case surrounds the compressor section, the combustor section, and the turbine section. The gas turbine engine also includes a means for providing an active variable cooling flow through a bypass duct external to the engine case to a secondary flow cavity of the turbine section.