Turbine Vane Cooling Microcircuit Design
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Solution Overview
Problem
Turbine engine components, particularly turbine vanes, face high thermal loads on the suction side and issues with cooling film exit holes being plugged by contaminants, leading to reduced cooling effectiveness.
Innovation Solution
A cooling microcircuit is designed with fluid exit holes positioned ahead of the gage or throat point, featuring curved inlets to accelerate cooling fluid, a long transverse passageway to maintain velocity, and refresher re-supply holes to prevent plugging, using refractory metal sheets to form the microcircuit within the airfoil portion.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If cooling film exit holes are positioned at or behind the gage/throat point, then cooling coverage is improved, but aerodynamic performance deteriorates and exit plugging risk increases
Solution Approach 1:
The patent positions cooling film exit holes in a different spatial location (ahead of the gage/throat point) than conventional designs, utilizing the longitudinal dimension of the airfoil to resolve the conflict between cooling coverage and aerodynamic performance. This dimensional repositioning allows cooling flow to be delivered without interfering with the critical aerodynamic region at or behind the throat point.
2Reliability
If cooling exit holes are positioned ahead of the gage/throat point, then exit plugging is prevented, but cooling coverage of the suction side is reduced
Solution Approach 1:
The cooling system is segmented into multiple functional zones: cooling fluid acceleration zone (curved inlets), transverse transport zone (long passageway), and cooling delivery zone (exit holes ahead of gage point). This segmentation allows each zone to optimize for its specific function while collectively achieving both plugging resistance and adequate cooling coverage.
Solution Approach 2:
The cooling fluid is preliminarily accelerated and directed through curved inlets and long transverse passageways before reaching the exit holes. This preliminary action ensures high-velocity, contaminant-resistant flow is established before the fluid exits, preventing plugging while maintaining cooling effectiveness.
3Temperature
If conventional cooling circuits are used, then manufacturing is simpler, but cooling effectiveness under high thermal loads is insufficient
Solution Approach 1:
The cooling microcircuit is nested within the airfoil wall structure, with cooling passages and exit holes integrated into the component geometry. This nesting approach incorporates complex cooling functionality without adding external complexity, allowing advanced cooling performance while maintaining manufacturing feasibility through integrated 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
The solution enhances cooling efficiency and prevents exit plugging, ensuring effective cooling beyond the gage or throat point without impacting aerodynamic performance, thereby improving overall cooling performance.
Implementation Method 1
A cooling microcircuit (32) is provided within a wall (34) forming the suction side (14) to convectively cool the airfoil portion (10)
Implementation Method 2
Each of the fluid inlets (40) is curved so as to accelerate the cooling fluid as it enters the cooling microcircuit (32)
Data Source
AI summary
A turbine engine component (12) has an airfoil portion (10) with a suction side (14). The component (12) includes a cooling microcircuit (32) embedded within a wall structure forming the suction side (14). The cooling microcircuit (32) has at least one cooling film hole (36) positioned ahead of a gage point (38) for creating a flow of cooling fluid over an exterior surface of the suction side (14) which travels past the gage point (38).