Compressor Cooling Air Passage in Gas Turbine Engine
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Solution Overview
Problem
Gas turbine engines face challenges in increasing the overall pressure ratio of the compressor section without exceeding temperature thresholds, which can lead to premature wear or damage of components due to increased temperatures.
Innovation Solution
The implementation of a cooling air passage system within the gas turbine engine, featuring an airflow member extending from the high pressure spool assembly to the upstream compressor stage, which provides compressor cooling air through a series of airflow features and openings to cool components exposed to the core airflow path, thereby managing temperature and extending the lifespan of components.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If the overall pressure ratio of the compressor section is increased to enhance engine efficiency, then the pressure and temperature of the airflow increase, but the temperature of components exposed to the airflow exceeds safe thresholds causing premature wear or damage
Solution Approach 1:
The compressor section is divided into multiple stages with intermediate cooling passages. The airflow path is segmented into zones, with cooling air introduced at strategic locations between compression stages to progressively manage temperature rise rather than allowing uniform temperature increase throughout the compressor.
Solution Approach 2:
Cooling air passages act as intermediary channels that introduce cooler air from upstream stages to cool downstream compressor components. These passages serve as mediators between the hot compressed airflow and the components that would otherwise be overheated, transferring thermal energy away from critical parts.
2Temperature
If cooling passages are added to manage component temperatures, then component temperature is reduced, but the device complexity increases
Solution Approach 1:
The cooling passages are merged with the existing compressor structure, utilizing the same housing and component spaces. Rather than adding separate external cooling systems, the cooling channels are integrated into the compressor assembly, sharing structural elements and space with the compression airflow paths.
Solution Approach 2:
The compressor housing and structural components serve multiple functions: they contain the compression airflow paths while simultaneously housing the cooling air passages. The same structural elements that provide mechanical support and containment also function as thermal management conduits, reducing the need for additional dedicated cooling structures.
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 allows the high pressure compressor to reach higher pressures, enhancing the overall efficiency of the gas turbine engine by effectively cooling critical components and preventing thermal damage, thus maintaining performance and reliability.
Implementation Method 1
a cooling air passage system within the gas turbine engine... provides compressor cooling air through a series of airflow features and openings to cool components exposed to the core airflow path
Implementation Method 2
an airflow member extending from the rotor disk of the high pressure spool assembly to the rotor disk of the upstream compressor stage... to define in part a compressor cooling air passage
Data Source
AI summary
A gas turbine engine includes a combustion section and a compressor section, the compressor section including a high pressure compressor. The high pressure compressor includes an aft-most compressor stage and an upstream compressor stage, each of the aft-most compressor stage and the upstream compressor stage including a rotor disk. The gas turbine engine also includes a high pressure spool assembly, the high pressure spool assembly including a rotor disk, and an airflow member extending from the rotor disk of the high pressure spool assembly to the rotor disk of the upstream compressor stage of the high pressure compressor to define in part a compressor cooling air passage outward of the airflow member along a radial direction.