Turbomachine Blade Cooling Cavity Segmentation
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Aircraft turbine blades face increased heat from combustion gases due to improved engine performance, which existing cooling methods struggle to manage effectively, leading to degraded turbomachine performance and increased airflow consumption.
Innovation Solution
The design incorporates a blade with a serpentine main cavity and interposed side cavity to maximize heat exchange and limit airflow heating, allowing the main airflow to remain fresh and efficiently cool the airfoil while reducing the necessary airflow rate.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If cooling air is taken from the compressor to cool the turbine blades, then the blade cooling effectiveness is improved, but the turbomachine performance deteriorates due to increased airflow consumption
Solution Approach 1:
The cooling system is segmented into multiple independent cavities (first cavity, second cavity, third cavity) that can be supplied with cooling air from different sources. This allows optimized airflow management where critical areas receive adequate cooling while minimizing overall airflow consumption from the compressor.
Solution Approach 2:
Different cavities are assigned to cool different regions of the blade based on their thermal requirements. The first cavity cools the leading edge and pressure side, the second cavity cools the suction side, and the third cavity cools the trailing edge, allowing each region to receive appropriate cooling without over-cooling the entire blade.
2Power
If the combustion chamber temperature is increased to improve engine performance, then the power output is improved, but the blade cooling requirement increases
Solution Approach 1:
The blade cooling system is divided into multiple cavities that can be independently controlled and supplied with cooling air. This segmentation allows the system to handle higher thermal loads from increased combustion temperatures by distributing the cooling demand across multiple zones rather than relying on a single cooling pathway.
Solution Approach 2:
The cooling system utilizes a multi-dimensional cavity network within the blade structure, with cavities positioned at different locations (leading edge, pressure side, suction side, trailing edge) to provide comprehensive thermal management across the entire blade volume, enabling effective cooling at higher operating temperatures.
3Device complexity
If a single cavity configuration is used for blade cooling, then the device complexity is reduced, but the cooling efficiency is insufficient
Solution Approach 1:
The cooling system is divided into multiple cavities (first, second, and third cavities) with distinct functions and airflow paths. This segmentation improves cooling efficiency by allowing targeted cooling of different blade regions while maintaining manageable complexity through systematic organization of the cavity network.
Solution Approach 2:
The multiple cavities work together as an integrated cooling system that addresses various thermal challenges across the blade simultaneously. The first cavity handles leading edge and pressure side cooling, the second cavity manages suction side cooling, and the third cavity handles trailing edge cooling, creating a universal cooling solution for the entire blade structure.
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 configuration effectively limits airflow consumption while maintaining optimal cooling of the blade, reducing thermal heating and ensuring a lower temperature at the leading edge, thus enhancing turbomachine performance.
Implementation Method 1
the main cavity thus enables a main airflow circulating in the same to follow a relatively long path, which makes it possible to maximise heat exchanges between this main airflow and the walls delimiting the main cavity
Implementation Method 2
whereas the side cavity enables a heat shield to be formed between the entire main cavity and the pressure side wall, which is generally particularly hot, so as to limit heating of the main airflow through the pressure side wall
Data Source
AI summary
In order to limit the air flow required to cool its blade member, a blade for an aircraft turbomachine turbine includes, in its blade member, a main passage configured to collect a main air flow from an air inlet and to circulate it in the blade member, and a side passage located between the main passage and the pressure-side wall, while being separated from the main passage, wherein the side passage is configured to collect a side air flow from the air inlet and to circulate it in the blade member, the main passage having at least three portions connected together end-to-end to form a coil, the side passage being located between each of these portions and the pressure-side wall.