Contoured Airfoil Flow Surface Mitigates Bow Wave Pressure
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Solution Overview
Problem
Turbine engine airfoil assemblies face challenges with bow wave-induced pressure variances and hot gas ingestion into cavities, leading to aerodynamic losses and weight savings issues.
Innovation Solution
Incorporating a contoured flow surface with a trough forward of the airfoil leading edge and a bulge proximate the lead edge, which mitigates bow wave pressure gradients by shifting radial streamlines, reducing hot gas ingestion and allowing for shorter flow paths and weight savings.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Loss of energy
If a conventional airfoil assembly is used, then the structure is simple, but bow wave-induced pressure variances cause hot gas ingestion into cavities leading to aerodynamic losses
Solution Approach 1:
The flow surface is given different local qualities through the contoured configuration: a trough region forward of the leading edge with lower elevation and a bulge region proximate the leading edge with higher elevation. These localized variations in surface geometry create specific flow patterns that mitigate bow wave effects and reduce hot gas ingestion into cavities, thereby reducing aerodynamic losses without requiring complete redesign of the entire airfoil assembly
Solution Approach 2:
The invention applies curvature principles by creating a contoured flow surface with a trough (concave region) forward of the leading edge and a bulge (convex region) proximate the leading edge. These curved surface features alter the radial streamline patterns and pressure distribution, effectively managing the bow wave-induced pressure variances and preventing hot gas ingestion while maintaining aerodynamic performance
2Weight of moving object
If the flow path is shortened for weight savings, then weight is reduced, but aerodynamic performance may deteriorate
Solution Approach 1:
The invention changes the geometric parameters of the flow surface by introducing a contoured configuration with specific trough and bulge features. This parameter modification allows the flow path to be shortened for weight savings while the contoured surface maintains or improves aerodynamic performance by optimizing flow patterns and reducing losses, thus resolving the contradiction between weight reduction and performance maintenance
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 reduces aerodynamic losses, minimizes hot gas ingestion, and enables weight savings while maintaining or improving aerodynamic performance.
Implementation Method 1
bow wave that emanates from the lead edge of flow path obstructions such as airfoils. The bow wave generates a locally high pressure which can result in ingestion of hot gases into the cavity
Implementation Method 2
mitigates bow wave pressure gradients by shifting radial streamlines
Data Source
AI summary
A turbine engine stage includes a plurality of airfoils extending between an inner band and an outer band. Each airfoil in the plurality of airfoils can have an outer wall defining a pressure side and a suction side, with the outer wall extending between a leading edge and a trailing edge. An intervening flow passage is defined between two adjacent airfoils in the plurality of airfoils.