Outer Diameter Platform Cooling Holes for Gas Turbine Thermal Management
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Solution Overview
Problem
Gas turbine engine first stage vane outer diameter platforms experience thermal distress due to hot combustion gases, requiring effective cooling solutions to manage extreme temperatures and thermal fatigue.
Innovation Solution
The implementation of a specific arrangement of cooling holes on the outer diameter platform, strategically positioned and configured to direct coolant flow for film cooling and convective cooling, with groups of holes placed on the suction and pressure sides of the airfoil, including perpendicular rows and varying orientations to effectively reduce metal temperatures.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If cooling holes are added to the outer diameter platform, then thermal management is improved, but device complexity increases
Solution Approach 1:
The cooling system is segmented into multiple groups of cooling holes (first group, second group, third group, fourth group, fifth group) strategically positioned at different locations on the outer diameter platform. Each group serves specific cooling zones, allowing targeted thermal management while maintaining systematic organization that reduces overall complexity.
Solution Approach 2:
Different groups of cooling holes are positioned to address local thermal conditions at specific locations on the outer diameter platform. The first group is near the suction side, the second group near the pressure side and leading edge, the third group at the center, the fourth group at the trailing edge, and the fifth group at the leading edge. This localized approach optimizes cooling effectiveness without requiring a uniform complex pattern across the entire platform.
2Temperature
If multiple groups of cooling holes are positioned strategically, then cooling effectiveness is improved, but manufacturing precision requirements increase
Solution Approach 1:
The cooling holes are divided into five distinct groups with specific location requirements. Each group has defined positioning criteria (e.g., first group near suction side, second group near pressure side and leading edge). This segmentation allows manufacturing processes to focus on achieving precision for each group separately rather than requiring uniform high precision across all holes simultaneously.
Solution Approach 2:
The patent specifies that the cooling holes are positioned 'proximate' to various features (suction side, pressure side, leading edge, trailing edge, center) rather than requiring exact coordinate precision. This partial specification approach provides manufacturing flexibility while still achieving the necessary cooling effectiveness, reducing the stringency of precision requirements.
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 cooling hole arrangement effectively reduces the metal temperature of the outer diameter platform through film cooling and convection, enhancing the thermal management and operational efficiency of the gas turbine engine by strategically directing coolant flow to critical areas.
Implementation Method 1
The plurality of cooling holes may be configured to eject coolant in a direction that film cools gaspath exposed surfaces of the OD platform
Implementation Method 2
The plurality of cooling holes may be configured to eject coolant in a direction that film cools gaspath exposed surfaces of the OD platform
Data Source
AI summary
An airfoil component is described herein. The airfoil component may include an OD platform comprising a gaspath face and a non-gaspath face coupled together via a plurality of cooling holes. The airfoil component may include an airfoil extending in from the outer diameter platform. The plurality of cooling holes comprises a plurality of groups of cooling holes disposed in the outer diameter platform proximate a suction side of the airfoil and a pressure side of the airfoil.