Air Guide Cooling Forward Spool Member
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Solution Overview
Problem
Gas turbine engines generate excessive heat during operation, which can lead to material temperature limits being exceeded by the forward spool member, necessitating effective cooling solutions to maintain efficiency and longevity.
Innovation Solution
An air guide system is integrated into the gas turbine engine to direct a cooling airflow from between high and low pressure spools onto the radially inner side of the forward spool member, utilizing a guiding tube to swirl the air and turbulators to enhance heat transfer, thereby reducing the spool member's temperature.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If the gas turbine engine operates at high power, then the engine produces more thrust and power, but excessive heat is generated that exceeds material temperature limits of the forward spool member
Solution Approach 1:
The invention extracts hot combustion gases from the main flow path by routing them through a separate path that bypasses the forward spool member, thereby removing the heat source from the problematic area while maintaining engine power output
Solution Approach 2:
The invention introduces an intermediary cooling airflow path that carries cooler air from the compressor to the forward spool member, acting as a thermal mediator between the hot combustion zone and the temperature-sensitive spool member
2Temperature
If cooling airflow is directed onto the forward spool member, then the spool member temperature is reduced, but the complexity of the air guide system increases
Solution Approach 1:
The air guide system is designed to perform multiple functions: it directs cooling airflow to the forward spool member, manages hot gas routing, and maintains pressure differentials, thereby reducing the need for separate dedicated components for each function
Solution Approach 2:
The invention uses flexible seals and thin film barriers to create airflow paths and contain pressure differentials without requiring complex rigid structural components, simplifying the overall air guide system design
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 air guide system effectively cools the forward spool member, reducing its operating temperature and enhancing heat transfer, thus improving the engine's operational efficiency and extending the lifespan of critical components.
Implementation Method 1
utilizing a guiding tube to swirl the air
Implementation Method 2
enhance heat transfer
Implementation Method 3
direct a cooling airflow from between high and low pressure spools onto the radially inner side of the forward spool member
Data Source
AI summary
A gas turbine engine that defines a radial direction and axial direction. The gas turbine engine includes a compressor section that includes a high pressure compressor. The high pressure compressor includes an aft-most compressor stage. The aft-most compressor stage includes a rotor, a low pressure shaft, a high pressure shaft drivingly coupled to the high pressure compressor. The high pressure shaft includes a central spool member and a forward spool member. The forward spool member extending between the central spool member and the aft-most compressor stage. The aft-most compressor stage further includes an air guide coupled to the aft-most compressor stage and the high pressure shaft. The air guide and a radially inward side of the forward spool member together defines an air flow passage for providing a cooling air flow.