Multi-Airstream Cooling System for Gas Turbine Engine
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Solution Overview
Problem
Gas turbine engines face challenges in maintaining component longevity due to rising internal temperatures, as traditional cooling systems rely on a single airflow path that becomes overheated near the combustor chamber, limiting engine efficiency and durability.
Innovation Solution
A multi-airstream cooling system is introduced, featuring a discharge slot, bypass passage, tangential onboard injector (TOBI), and structural ribs, which enable multiple airflow paths to provide thermal separation and efficient cooling to different engine components, preventing overheating.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If a single airflow path is used for cooling, then the cooling system structure is simple, but the airflow temperature rises due to proximity to the combustor chamber
Solution Approach 1:
The cooling system is divided into multiple independent airflow paths (first, second, and third airflow paths) that separately cool different engine components. This segmentation allows each airflow path to be optimized independently, preventing the temperature rise issue in single-path systems while maintaining manageable structural complexity through modular design.
Solution Approach 2:
Different airflow paths are directed to specific locations requiring cooling: the first path cools the combustor liner, the second path cools turbine blades via TOBI, and the third path cools stator vanes. This local quality approach ensures that cooling is provided precisely where needed with appropriate temperature characteristics, preventing overall airflow temperature rise while addressing specific thermal requirements.
2Temperature
If multiple airflow paths are used for cooling, then the airflow temperature can be maintained lower, but the cooling system structure becomes complex
Solution Approach 1:
Multiple airflow paths and cooling functions are merged into a single integrated cooling system structure. The inner vane support, flow guide, and fastened inner duct work together as unified components that simultaneously manage multiple airflow paths, reducing the need for separate complex structures for each cooling function while maintaining lower airflow temperatures through multi-path design.
Solution Approach 2:
The cooling system components are designed with multi-functionality: the inner vane support structure serves both structural and cooling airflow management functions, the flow guide directs multiple airflow paths through a single component, and the fastened inner duct provides both containment and cooling functions. This universality reduces overall system complexity despite the presence of multiple airflow paths.
3Reliability
If cooling airflow is increased to protect components, then component durability is improved, but engine efficiency decreases
Solution Approach 1:
Cooling airflow is applied locally and selectively to specific components that require it (combustor liner, turbine blades, stator vanes) rather than increasing overall engine cooling airflow. This targeted approach protects component durability where thermal exposure is highest while minimizing the impact on overall engine efficiency by avoiding unnecessary cooling airflow increases in other areas.
Solution Approach 2:
The cooling system utilizes engine's own operational parameters (existing airflow paths and pressure differentials) to provide cooling without requiring additional energy input or significant airflow increases. The system self-regulates cooling delivery based on component thermal needs, maintaining durability while preserving engine efficiency by avoiding excessive cooling airflow that would reduce productivity.
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 multi-airstream cooling system effectively maintains component durability and increases engine efficiency by providing cooler airflow to various sections of the gas turbine engine, ensuring optimal performance and longevity.
Implementation Method 1
Gas turbine engines may depend on a cooling airflow to protect components and ensure longevity. The cooling air may rise in temperature due to the location of the airflow path being in close proximity to the combustor chamber.
Implementation Method 2
A multi-airstream cooling system is introduced, featuring a discharge slot, bypass passage, tangential onboard injector (TOBI), and structural ribs, which enable multiple airflow paths to provide thermal separation and efficient cooling to different engine components
Data Source
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AI summary
The invention is related to a multi-air stream cooling system (200) for a gas turbine engine. The cooling system (200) comprises a vane support (210), a flow guide (220) connected to the vane support (210) at a radially inner side and an inner duct (230), connected to a radially inner side of the flow guide (220). A first flowpath (E) is defined between a comustor liner (191) and the vane support (210) and an inner diffuser case (190). A second flow path (F) is defined between the inner diffuser case (190), the inner vane support (210) and the flow guide (220). A third flowpath (G) is defined between the flow guide (220) and an inner duct (230) which is arranged at a radially inner side of the flow guide (220). Thus, the provision of a cooling flow to a turbine nozzle is possible without increasing the airflow temperature.