Airfoil Acute-Angle Cooling Flow Paths for Thermal Stress Reduction
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Solution Overview
Problem
Gas turbine engine airfoils face reduced useful life due to thermal stresses from high combustion gas temperatures, and existing cooling methods decrease engine efficiency by lowering combustion gas temperature.
Innovation Solution
The airfoil design features an internal cooling flow passage with flow paths oriented at acute angles to slow and distribute cooling air effectively, reducing thermal stress and maintaining engine efficiency by minimizing cooling air discharge rate.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Duration of action of stationary object
If cooling air is discharged from apertures of the airfoils to withstand temperature increase in combustion gas flow, then the useful life of the airfoils is improved, but the temperature of the combustion gases is lowered, thereby decreasing engine operating efficiency
Solution Approach 1:
The patent changes the geometric parameters of the cooling flow paths, specifically orienting them at acute angles (e.g., 30-60 degrees) relative to the passage axis. This parameter change optimizes the cooling air discharge characteristics to reduce thermal stress on airfoils while minimizing the amount of cooling air required, thereby maintaining engine operating efficiency.
Solution Approach 2:
The patent applies different flow path orientations at different locations within the airfoil structure. By varying the acute angle orientation of flow paths in different regions, the cooling effect is optimized locally where thermal stresses are highest, while reducing overall cooling air consumption to maintain combustion gas temperature and engine efficiency.
2Strength
If cooling air is discharged into the combustion gas flow to cool the airfoils, then thermal stress on airfoils is reduced, but the combustion gas temperature decreases, thereby detracting from operating efficiencies
Solution Approach 1:
The patent modifies the flow path geometry by orienting paths at acute angles to the passage axis, which changes how cooling air is discharged. This parameter change enables effective thermal stress reduction on airfoils while minimizing the parasitic cooling effect on combustion gases, thereby preserving engine productivity and operating efficiency.
3Reliability
If more cooling air is discharged to better cool the airfoils and increase their useful life, then the durability of airfoils is improved, but the engine operating efficiency decreases due to lower combustion gas temperature
Solution Approach 1:
The patent optimizes the flow path orientation parameters to achieve effective cooling with minimal air discharge. By setting acute angles between flow paths and passage axis, the cooling air is more efficiently utilized to protect airfoil durability while minimizing the energy penalty on engine operating 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 design enhances airfoil durability and maintains engine efficiency by reducing metal temperatures and thermal gradients, achieving lower airfoil metal temperatures with reduced cooling flow discharge, thereby improving specific fuel consumption.
Implementation Method 1
a plurality of flow paths extending through at least one of the sides such that the flow paths are configured to discharge cooling air from the passage, wherein each of the flow paths has a broken flow path axis oriented to intersect the passage axis at an acute angle
Implementation Method 2
This design enhances airfoil durability and maintains engine efficiency by reducing metal temperatures and thermal gradients
Implementation Method 3
an internal cooling flow passage defined between the sides, wherein the passage has a passage axis along which cooling air is to flow
Data Source
AI summary
An airfoil includes a leading edge, a trailing edge, and a pair of sides extending from the leading edge to the trailing edge. The airfoil also includes an internal cooling flow passage defined between the sides, wherein the passage has a passage axis along which cooling air is to flow. The airfoil further includes a plurality of flow paths extending through at least one of the sides such that the flow paths are configured to discharge cooling air from the passage, wherein each of the flow paths has a broken flow path axis oriented to intersect the passage axis at an acute angle.