Gas Turbine Thermally Isolated Cooling Section
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Solution Overview
Problem
Gas turbine engine components, particularly in the high pressure turbine section, are inefficiently cooled using multiple separate flows of cooling fluid, which limits their operating temperature and efficiency.
Innovation Solution
A thermally isolated area within the gas turbine engine is created, bounded by specific seals and walls, and cooled using a single inlet of cooling fluid from a common source, which is directed to exit through rotor blades, allowing for efficient cooling of the components.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If multiple separate flows of cooling fluid are used to cool turbine components, then the cooling coverage is improved, but the device complexity and manufacturing difficulty increase
Solution Approach 1:
The patent merges multiple separate cooling fluid flows into a single common cooling passage that supplies cooling fluid to multiple turbine components (rotor disks, stator blades, and rotor blades) through a unified pathway, reducing system complexity while maintaining comprehensive cooling coverage
Solution Approach 2:
The common cooling passage serves multiple functions by delivering cooling fluid to various locations including the first rotor disk, second rotor disk, stator blades, and rotor blades, making the cooling system multi-functional and reducing the need for separate dedicated cooling passages for each component
2Reliability
If multiple separate flows of cooling fluid are used to cool turbine components, then the cooling effectiveness is improved, but the manufacturing precision requirements increase
Solution Approach 1:
By consolidating multiple cooling passages into one common cooling passage with properly positioned inlets, the patent reduces the cumulative precision requirements that would arise from manufacturing multiple separate passages, while still achieving effective cooling through the unified structure
3Reliability
If components are cooled to maximum rated temperature, then the operating safety is improved, but the fuel efficiency and power output are reduced
Solution Approach 1:
The patent changes the temperature parameter by enabling the turbine components to operate at temperatures above the traditional maximum rated temperature through improved cooling mechanisms, allowing higher operating temperatures that increase fuel efficiency and power output while maintaining safety through the common cooling passage 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
This approach enables the components to be cooled below their maximum rated temperature, allowing the engine to operate at higher temperatures, increasing fuel efficiency and reducing component size while maintaining thrust.
Implementation Method 1
the components of the turbine section are cooled with cooling fluid
Implementation Method 2
a thermally isolated area, and a first rotor disk and a second rotor disk. Each of the first and second rotor disks are provided within the thermally isolated area
Data Source
AI summary
A section of a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a thermally isolated area, and a first rotor disk and a second rotor disk. Each of the first and second rotor disks are provided within the thermally isolated area.