Turbomachine Blade Trailing Edge Cooling Partition Curvature
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Solution Overview
Problem
The existing turbine blade cooling designs for turbomachines, particularly in turbojet engines, suffer from non-uniform cooling at the trailing edge, leading to hot spots near the blade tip due to air recirculation and inadequate air distribution through cooling slits.
Innovation Solution
A turbine blade design featuring a cooling circuit with a conduit, duct, and manifold separated by a partition, where the partition's curvature directs air flow more efficiently to the trailing edge slits, reducing recirculation and enhancing cooling by using curved flow disturbers and straight reliefs to improve air distribution and heat exchange.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If a conventional cooling circuit with duct and manifold is used, then cooling is provided to the trailing edge, but air recirculation occurs causing non-uniform cooling and hot spots near the blade tip
Solution Approach 1:
The partition includes a first portion with a curved shape concave towards the trailing edge, which redirects the airflow to prevent recirculation and ensure uniform cooling distribution to the trailing edge slits, eliminating hot spots near the blade tip
2Device complexity
If the partition is straight, then the structure is simple, but air flow recirculates towards mid-height slits instead of reaching tip slits
Solution Approach 1:
The partition incorporates a curved first portion that efficiently redirects airflow toward the trailing edge slits without requiring complex additional components, achieving improved cooling efficiency with minimal structural complexity
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 design significantly improves cooling uniformity at the trailing edge by directing air flow effectively to hot spots, reducing recirculation and enhancing heat exchange, thereby maintaining optimal blade temperature and performance.
Implementation Method 1
The turbine blades are cooled by circulating air in each blade, drawn off upstream from the combustion chamber into the blade root, this air being evacuated through drillings passing through the walls of these blades to cool them, and through slits passing through their trailing edge to cool them.
Implementation Method 2
The turbine blades are cooled by circulating air in each blade
Implementation Method 3
Due to the curvature of the partition close to the tip, the end of this partition is brought closer to the trailing edge, which limits recirculation in the fluid manifold leading from the duct.
Data Source
AI summary
A turbine blade includes a root and an airfoil extending from a base, through which it is connected to the root, to a tip. The airfoil includes an intrados wall and an extrados wall, connected by a leading edge and by a trailing edge with a cooling circuit. The cooling circuit includes a conduit with a duct and a manifold prolonging this conduit. The conduit collects air from the blade root to supply the duct and the manifold that is located downstream from the duct and that supplies the slits in the trailing edge with air. The duct supplies air to one end of the manifold close to the tip. The manifold is separated from the duct by a partition including a portion close to the tip that is curved to be concave when seen from the trailing edge.