Turbine Stator Vane Cavity Partitioning for Leading-Edge Film Cooling
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Solution Overview
Problem
In turbine stator vanes, the pressure surface side and suction surface side of the leading edge experience different fluid pressures, leading to excessive cooling air flow rates through suction surface side film cooling holes, which decreases gas turbine efficiency.
Innovation Solution
The internal space of the turbine stator vane is partitioned by first and second partition walls into pressure and suction surface leading edge cavities, with through-holes opening into these cavities to optimize cooling air distribution, using angled intersections and insert members for efficient cooling.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If film cooling holes are provided in both pressure surface side vane wall and suction surface side vane wall using the same cavity cooling air, then both surfaces can be cooled, but the cooling air flow rate from the suction surface side film cooling hole becomes excessive
Solution Approach 1:
The internal cooling cavity is divided into a pressure surface side cavity and a suction surface side cavity by introducing a partition wall. This segmentation allows independent control of cooling air flow to each surface, preventing excessive cooling air flow from the suction surface side while maintaining adequate cooling on the pressure surface side.
Solution Approach 2:
Different cooling air flow rates are provided to the pressure surface side and suction surface side by independently controlling the cooling air supply to each cavity. The partition wall enables localized cooling air distribution according to the specific cooling requirements of each surface, with the pressure surface side receiving more cooling air and the suction surface side receiving controlled cooling air.
2Device complexity
If the same cooling air cavity is used for both pressure surface side and suction surface side, then the structure is simple, but the cooling air distribution is unoptimized
Solution Approach 1:
The single cooling cavity is segmented into two separate cavities (pressure surface side cavity and suction surface side cavity) using a partition wall. This segmentation enables optimized cooling air distribution to each surface while maintaining a relatively simple overall structure that can be integrated into the existing vane 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
This configuration optimizes cooling air distribution, reducing excessive flow rates and enhancing gas turbine efficiency by ensuring adequate cooling while minimizing air usage.
Implementation Method 1
a first partition wall and a second partition wall that partition an internal space of an airfoil... partitions the internal space into a pressure surface side leading edge cavity and a suction surface side leading edge cavity
Implementation Method 2
a turbine stator vane configured such that a vane wall is film-cooled by cooling air ejected from an internal space of an airfoil via a film cooling hole
Data Source
AI summary
A turbine stator vane includes a first partition wall and a second partition wall which partition the internal space of an airfoil, and a plurality of through-holes penetrating a vane wall constituting the airfoil. The first partition wall extends from the vane wall on the pressure side of the airfoil to the vane wall on the negative pressure side of the airfoil, and is provided at the position nearest to the leading edge. The second partition wall extends from the vane wall on the leading edge side of the airfoil to the first partition wall, and partitions the internal space into a pressure-side leading edge cavity and a negative pressure-side leading edge cavity. An intersection angle between a first virtual straight line and the extending direction of the vane wall is an obtuse angle at the leading edge and an acute angle at the trailing edge.