Intercooled Nozzle Guide Vane Cooling With Split Secondary Airflow
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Solution Overview
Problem
Gas turbine engines face challenges in effectively cooling components due to rising internal temperatures, particularly in the turbine section, as conventional cooling systems struggle to manage temperature increases caused by compressor airflow.
Innovation Solution
A gas turbine engine design incorporating an annular diffuser, intercooler heat exchanger, and tangential onboard injector (TOBI) system to direct cooling airflow through specific zones of the HPT stator vanes, utilizing both diffuser and intercooler air to cool different regions of the vanes, enhancing temperature management.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If conventional cooling systems are used in gas turbine engines, then the system structure is simple, but the cooling effectiveness is insufficient due to rising internal temperatures
Solution Approach 1:
The cooling system is segmented into multiple independent airflow paths: a first cooling airflow path for cooling the leading edge region of HPT stator vanes, and a second cooling airflow path for cooling the trailing edge region. This segmentation allows each path to be optimized for its specific cooling zone, improving overall cooling effectiveness while maintaining manageable system complexity through modular design
Solution Approach 2:
Different regions of the HPT stator vanes are provided with different cooling airflows tailored to their specific thermal requirements. The leading edge region receives cooling airflow from the first path, while the trailing edge region receives cooling airflow from the second path. This local differentiation of cooling quality addresses the varying temperature distributions across different vane regions, enhancing overall cooling effectiveness
2Reliability
If a single cooling airflow path is used, then the system is simple, but it cannot effectively cool different regions of the HPT stator vanes
Solution Approach 1:
The cooling airflow is segmented into distinct paths that deliver cooled air to different regions of the HPT stator vanes. The first cooling airflow path delivers cooling airflow to the leading edge region, while the second cooling airflow path delivers cooling airflow to the trailing edge region. This segmentation enables region-specific temperature control, improving overall temperature management effectiveness
Solution Approach 2:
Each region of the HPT stator vanes is provided with cooling airflow of appropriate quality for its specific thermal conditions. The leading edge region and trailing edge region receive differentiated cooling treatments through separate airflow paths, ensuring that each local region achieves optimal temperature control tailored to its operational requirements
3Temperature
If cooling airflow is not intercooled, then the system is simpler, but the cooling air temperature is too high to be effective
Solution Approach 1:
A heat exchanger is introduced as an intermediary component between the diffuser and the cooling airflow paths. This heat exchanger acts as a mediator that transfers heat from the cooling airflow to the surrounding environment, reducing the temperature of the cooling air before it is delivered to the HPT stator vanes. This intermediary cooling mechanism enables effective temperature reduction without requiring complete redesign of the cooling system 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
The system effectively cools the HPT stator vanes by using diffuser OD flow for leading edge regions and intercooler air for trailing edge regions, improving temperature control and extending component longevity.
Implementation Method 1
The heat exchanger is configured to selectively cool a portion of the diffuser gas-intercooler gas
Implementation Method 2
A first portion of the intercooler gas is directed through the ICF passage and into the HPT stator vanes
Data Source
AI summary
A gas turbine engine is provided that includes compressor and combustor sections, inner and outer casings, an annular diffuser, an inner diffuser casing, a heat exchanger, and an HPT stator vane stage. An annular combustor is disposed radially inward of the outer casing and has inner and outer radial wall structures. The outer casing and the combustor outer radial wall structure define a diffuser OD flow path. The annular diffuser directs diffuser gas towards the combustor section. The inner diffuser casing is disposed radially inward of the annular combustor and spaced apart from the combustor inner radial wall structure. The inner casing is disposed radially inward of and spaced apart from the inner diffuser casing. The inner diffuser casing and the inner casing define an ICF passage. The heat exchanger is configured to produce intercooler gas. Intercooler gas is directed through the ICF passage and into the HPT stator vanes.