Helicopter Turbine Blade Cooling via Segmented Internal Circuits
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Solution Overview
Problem
High pressure turbine blades in turboshaft engines face challenges in temperature resistance due to increasing combustion gas temperatures, requiring enhanced cooling methods to maintain performance while minimizing fabrication costs.
Innovation Solution
A high pressure turbine blade design featuring an internal cooling circuit with separate upstream ducts and central chambers, optimized for cooling different blade sections, and strategically positioned cooling holes to enhance ventilation efficiency and reduce fabrication costs.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If a single internal cooling circuit is used in the blade, then the fabrication process is simpler, but the cooling efficiency is insufficient to handle increasing combustion gas temperatures
Solution Approach 1:
The internal cooling circuit is segmented into two independent circuits: a first internal cooling circuit with upstream ducts dedicated to cooling the leading edge and upper surface, and a second internal cooling circuit with a central chamber dedicated to cooling the pressure wall and trailing edge. This segmentation allows each circuit to be optimized for specific blade regions, improving overall cooling efficiency without requiring a completely complex new design.
Solution Approach 2:
Different regions of the blade are provided with tailored cooling solutions through the segmented circuits. The first circuit with upstream ducts specifically targets the leading edge and upper surface, while the second circuit with the central chamber targets the pressure wall and trailing edge. This local quality approach ensures that each critical region receives appropriate cooling based on its specific thermal demands.
2Temperature
If separate upstream ducts and central chamber are used for cooling different blade sections, then cooling efficiency is improved, but fabrication cost increases
Solution Approach 1:
The cooling system is divided into two independent circuits that can be designed and manufactured separately, allowing for optimized fabrication processes for each circuit while maintaining overall cooling efficiency. The upstream ducts and central chamber are distinct components that can be produced using different manufacturing techniques suited to their specific geometric requirements.
Solution Approach 2:
The design allows for independent adjustment and optimization of each cooling circuit based on operational requirements. The upstream ducts and central chamber can be independently modified, maintained, or replaced without affecting the other circuit, providing dynamic flexibility that can reduce long-term fabrication and maintenance costs.
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
The design improves cooling efficiency and reduces fabrication costs by allowing independent cooling adjustments and optimized air flow, effectively managing temperature resistance and mechanical strength.
Implementation Method 1
This air is inlet at the root of the blade and is routed along an internal circuit in the blade to cool it
Implementation Method 2
it is evacuated outside the blade through holes passing through the walls of this blade and distributed on these walls
Implementation Method 3
These holes are used to evacuate cooling air, and to create an air film on the external surface of the blade that is colder than combustion gases that contribute to limiting the temperature of the blade
Data Source
AI summary
A blade of a high-pressure turbine of a turboshaft engine, the blade including an airfoil extending in a spanwise direction, terminating in an apex and having a suction wall and a pressure wall joined by a leading edge and joined by a trailing edge. The blade further includes an internal cooling circuit having only an upstream duct and a central chamber for cooling the blade by circulating air. The upstream duct and the central chamber are separately supplied with air. The upstream duct being dedicated to the cooling of the leading edge and the suction wall, and the central chamber being dedicated to the cooling of the pressure wall and the trailing edge and being provided with bridge elements each connecting the pressure wall and the suction wall.