Non-Axisymmetric Turbine Endwall Contouring for Vortex Loss Reduction
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Solution Overview
Problem
Gas turbine engines suffer from endwall losses due to the formation of vortices in the fluid flow passages between airfoils, which are not effectively mitigated by existing technologies.
Innovation Solution
The endwalls are contoured with specific features such as depressions and peaks to reduce endwall losses, featuring three distinct configurations on the inner and outer endwalls to minimize vortex formation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Loss of energy
If conventional smooth endwalls are used in turbine sections, then the structure is simple and easy to manufacture, but secondary losses increase due to vortex formation in the fluid flow passages
Solution Approach 1:
The endwall is designed with non-axisymmetric contouring features including peaks and valleys at specific locations rather than uniform smoothing. These localized geometric variations are positioned to specifically address vortex formation in critical flow passage regions while maintaining simplicity in other areas, thus reducing secondary losses without excessive complexity
Solution Approach 2:
The invention employs non-axisymmetric endwall contouring where the endwall geometry varies asymmetrically around the circumference. This asymmetric shaping creates favorable flow conditions in specific regions by disrupting vortex formation patterns, directly addressing the energy loss problem while introducing controlled geometric complexity
2Loss of energy
If endwall contouring features are added to reduce vortices, then secondary losses decrease, but manufacturing complexity increases
Solution Approach 1:
The endwall contouring is defined by specific geometric parameters including peak heights, valley depths, and circumferential positions that can be systematically controlled during manufacturing. By standardizing these parameters and using consistent contouring patterns, the invention reduces endwall losses while making the manufacturing process more predictable and manageable
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
The endwall contouring significantly reduces secondary losses by minimizing vortex formation, enhancing the efficiency of gas turbine engines.
Implementation Method 1
a flow phenomenon known as a vortex, which forms as a result of the boundary layer separating from the endwall as the gas passes the airfoils
Implementation Method 2
the boundary layer separating from the endwall as the gas passes the airfoils
Data Source
Figure 1
Figure 2A
Figure 2B
AI summary
A turbine section (28, 34) includes a pair of adjacent turbine airfoils (59A, 59B) and an endwall (64A, 64B) extending between the airfoils (59A, 59B). The endwall (64A, 64B) includes a first feature (80) spanning approximately thirty percent pitch (P) and having a first depression (82) with a maximum depression located between twenty percent and eighty percent of the axial chord length (76) of the first airfoil (59A), a second feature (86) spanning approximately thirty percent pitch (P) and having a first peak (88) with a maximum height (90) located between sixty percent and ninety percent of the axial chord length (76) of the first airfoil (59A), and a third feature (92) spanning approximately thirty percent pitch (P) and having a second depression (94) with a maximum depression located between twenty percent and fifty percent of the axial chord length (76) of the second airfoil (59B).