Turbine Blade Cooling Hole Side Wall Angle Optimization
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Solution Overview
Problem
Existing cooling hole designs in gas turbine engine turbine blades often result in inefficient cooling due to their orientation and geometry, particularly as they tend to be long and connect to the trailing edge at a steep angle, which can lead to suboptimal flow distribution and cooling effectiveness.
Innovation Solution
The design of a cooling hole that extends from a pocket underneath the platform to the side wall at a controlled angle, typically between 5 and 30 degrees, ensuring reliable air supply to the side wall and trailing edge, with an elongated or oval shape at the ends to facilitate better flow distribution.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Area of stationary object
If cooling holes are designed to be long and connect to the trailing edge at a steep angle, then the cooling coverage area is increased, but the flow distribution becomes suboptimal and cooling effectiveness decreases
Solution Approach 1:
The patent changes the geometric parameters of the cooling hole, specifically the angle relative to the side wall (5-30 degrees) and the cross-sectional shape (elongated or oval), to optimize both flow distribution and cooling effectiveness simultaneously
Solution Approach 2:
The cooling hole cross-section is designed with non-circular elongated or oval geometry to create localized flow distribution patterns that match the thermal requirements of different regions of the side wall and trailing edge
2Strength
If cooling holes are oriented at steep angles to the trailing edge, then the structural integrity is maintained, but the airflow distribution to the side wall becomes inefficient
Solution Approach 1:
The patent optimizes the orientation angle parameter of the cooling hole (5-30 degrees relative to the side wall) to achieve an optimal balance between structural integrity and airflow distribution efficiency
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 enhances cooling efficiency by providing consistent airflow to the side and trailing edges of the turbine blade, improving heat management and reducing thermal stress on the blade.
Implementation Method 1
cooling air is supplied to a pocket formed on the pressure side of the turbine blade platform. The cooling air flows from the pocket through a cooling hole to a side wall of the turbine blade
Implementation Method 2
providing consistent airflow to the side and trailing edges of the turbine blade, improving heat management and reducing thermal stress on the blade
Data Source
Figure 1
Figure 2A
Figure 2B~2C
AI summary
A turbine blade (102) includes an airfoil (106) including a pressure side (107) and a suction side (109). A platform (108) includes a pressure side wall (92) and a suction side wall (94), and has a leading edge end wall (88) and a trailing edge end wall (90). A pocket (108) is positioned under the platform (108) on the pressure side (107). A hole (128) has a first end (130) communicating with the pocket (108) and having a second end (132) communicating with the pressure side wall (92). A gas turbine engine (20) is also disclosed.