Turbine Airfoil Film Cooling via Sidewall Diffuser
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Solution Overview
Problem
High temperatures in certain regions of gas turbine engines lead to increased wear and tear, reducing the lifespan of components and affecting efficiency.
Innovation Solution
A cooling system is implemented in the turbine, where a cooling fluid is directed through passages in the airfoil and diffusers to form a film on the sidewalls, particularly at high temperature regions, reducing thermal exposure and oxidation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If high combustion temperatures are used in the turbine, then combustion efficiency and power production are improved, but component wear increases and component life decreases
Solution Approach 1:
A cooling fluid is introduced as an intermediary substance between the hot combustion gases and the turbine airfoil/sidewall. The cooling fluid flows through passages in the airfoil and along the sidewall surface, forming a protective film that mediates the thermal interaction, allowing high combustion temperatures to be maintained while protecting components from excessive heat
2Reliability
If cooling fluid is directed through passages in the airfoil and diffusers to form a film on sidewalls, then component life is extended and temperature uniformity is improved, but device complexity increases
Solution Approach 1:
The cooling system is segmented into multiple independent components: cooling fluid passages within the airfoil structure, diffusers positioned at specific locations, and film formation zones along the sidewall. This segmentation allows each component to be optimized independently and facilitates maintenance while achieving comprehensive cooling coverage
Solution Approach 2:
The cooling approach transitions from a single-dimension approach (cooling only the airfoil) to a multi-dimensional solution by adding sidewall cooling through diffusers. This creates a two-dimensional cooling surface (airfoil + sidewall) that more effectively manages heat distribution and protects high-temperature regions
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 method extends the life of turbine components, improves temperature uniformity, and enhances overall engine performance by directing more compressed air for mechanical output while reducing thermal fatigue.
Implementation Method 1
a first passage in the airfoil proximate a high temperature region, the first passage configured to receive a cooling fluid... a first diffuser in fluid communication with the first passage, the first diffuser configured to direct the cooling fluid to form a film on a surface of the first sidewall
Data Source
AI summary
According to one aspect of the invention, a turbine includes a first sidewall, an airfoil positioned between the first sidewall and a second sidewall and a first passage in the airfoil proximate a high temperature region, the first passage configured to receive a cooling fluid, wherein the high temperature region is near an interface of the first sidewall and a trailing edge of the airfoil. The turbine further includes a first diffuser in fluid communication with the first passage, the first diffuser configured to direct the cooling fluid to form a film on a surface of the first sidewall.