Turbine Film Cooling Hole with Conical Diffusing Section
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Solution Overview
Problem
Turbine engine cooling methods, such as film cooling, reduce efficiency by bleeding air from the compressor, and existing cooling technologies do not effectively manage high temperatures in hot gas path components without compromising performance.
Innovation Solution
A method of forming film holes in turbine engine components with a layup portion and applying a coating to fill the layup portion, creating a film hole with a predetermined inner dimension, which enhances thermal insulation and aerodynamic flow by optimizing the coating application on the conical diffusing section.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If film cooling holes are formed in turbine engine components to provide thermal insulation, then the component can withstand high temperatures, but the cooling process reduces engine efficiency by bleeding air from the compressor
Solution Approach 1:
The patent applies parameter changes by modifying the geometric parameters of the film cooling hole, specifically creating a conical diffusing section with an expanding cross-sectional area from inlet to outlet. This geometric transformation optimizes the cooling film discharge characteristics, improving thermal insulation effectiveness while minimizing the amount of cooling air required, thus reducing the energy loss to the compressor bleed air.
2Reliability
If a coating is applied to the film cooling hole to prevent thermal damage, then the component durability is enhanced, but the manufacturing complexity increases
Solution Approach 1:
The patent incorporates the conical diffusing section geometry into the film cooling hole structure during the initial manufacturing process, before the component is put into service. This preliminary action ensures that the optimal cooling film discharge characteristics are built-in from the start, eliminating the need for additional complex coating applications or post-manufacturing modifications to achieve the desired thermal protection and flow optimization.
3Loss of energy
If the film cooling hole has a larger inner dimension to improve cooling effectiveness, then more cooling air can be discharged, but the component wall thickness and strength are compromised
Solution Approach 1:
The patent transitions from a simple cylindrical film cooling hole to a conical diffusing section that expands in the radial dimension from inlet to outlet. This dimensional change allows the cooling hole to discharge a greater volume of cooling air effectively, improving cooling effectiveness without requiring a proportionally larger hole diameter throughout its length, thus preserving component wall thickness and structural strength.
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 approach improves thermal insulation and maintains aerodynamic flow efficiency by ensuring the coating optimally fills the layup portion, reducing thermal damage and enhancing the effectiveness of film cooling without compromising engine performance.
Implementation Method 1
A coating, such as a thermal barrier coating can be placed on portions of the film cooling hole to prevent thermal damage due to high temperatures
Implementation Method 2
A typical film cooling hole is a cylindrical bore inclined at a shallow angle through the heated wall for discharging a film of cooling air along the external surface of the wall to provide thermal insulation against the flow from hot combustion gases
Data Source
AI summary
An apparatus and method relating to a film hole of a component of a turbine engine comprising including forming the hole in the component and applying a coating to the component such that the coating fills in portions of the film hole.