Gas Turbine Thermally Isolated Area Cooling
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Solution Overview
Problem
Gas turbine engines face inefficiencies in cooling the high pressure turbine components, which limits their operating temperature and fuel efficiency, and results in mechanical stress due to high-speed spool rotation and larger core sizes.
Innovation Solution
A thermally isolated area within the high pressure turbine section is cooled using a common flow of cooling fluid from a single source, directed through a tangential onboard injector and sealed to prevent core airflow entry, allowing for overcooling of components and efficient heat management.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If multiple separate flows of cooling fluid are used to cool high pressure turbine components, then cooling coverage is improved, but system complexity and mechanical stress increase
Solution Approach 1:
The patent combines multiple separate cooling flows into a single common cooling flow that is directed through a tangential onboard injector. This single flow serves multiple cooling purposes within the thermally isolated area, reducing the number of separate cooling systems while maintaining comprehensive cooling coverage of the high pressure turbine components.
Solution Approach 2:
The common cooling flow performs multiple functions simultaneously: it cools the turbine components, manages heat within the thermally isolated area, and reduces mechanical stress on the spool. This multi-functional approach eliminates the need for separate dedicated cooling systems for each function.
2Use of energy by moving object
If higher operating temperatures are achieved, then fuel efficiency is improved, but component thermal stress and mechanical stress increase
Solution Approach 1:
The patent applies preliminary cooling to the high pressure turbine components before they are subjected to high operating temperatures. The common cooling flow is introduced into the thermally isolated area in advance, creating a protective thermal environment that allows the engine to operate at higher temperatures without the components experiencing excessive thermal stress.
Solution Approach 2:
The patent changes the thermal parameters of the turbine components by maintaining lower component temperatures through active cooling while allowing the gas path temperatures to be higher. This decoupling of gas path temperature from component temperature enables higher fuel efficiency without proportionally increasing mechanical stress on the components.
3Device complexity
If core airflow is allowed to enter the thermally isolated area, then cooling fluid distribution is simplified, but temperature control precision deteriorates
Solution Approach 1:
The patent segments the turbine interior into a thermally isolated area and the rest of the core airflow path. This segmentation is achieved through sealing structures that prevent core airflow from entering the thermally isolated area, allowing independent temperature control and cooling fluid management within the isolated region.
Solution Approach 2:
The patent introduces a common cooling flow as an intermediary substance that is directed through a tangential onboard injector into the thermally isolated area. This cooling flow acts as a mediator that provides precise temperature control without being mixed with the core airflow, maintaining temperature control precision while simplifying the cooling fluid distribution system.
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 cooling scheme enables the gas turbine engine to operate at higher temperatures, increasing fuel efficiency, reducing component size, and relaxing mechanical stress on the high speed spool, while maintaining or improving thrust performance.
Implementation Method 1
the components of the turbine section are typically cooled with cooling fluid
Implementation Method 2
a thermally isolated area within the high pressure turbine section is cooled using a common flow of cooling fluid
Data Source
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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.