Arcuate Turbine Vane Platforms for Combustor Interface Flow
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Solution Overview
Problem
The interface between the combustor and turbine sections in gas turbine engines experiences flow stagnation and bow wave effects due to geometric issues, leading to increased thermal loads and oxidation of components, which affects durability.
Innovation Solution
The design incorporates arcuate outer and inner vane platforms that follow the contours of the combustor liner panels, creating a smooth flow path and minimizing pressure gradients, along with effusion cooling to reduce thermal loads and secondary flow effects.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If conventional interface geometry is used between combustor and turbine sections, then structural simplicity is maintained, but flow stagnation and bow wave effects occur leading to increased thermal loads and oxidation
Solution Approach 1:
The patent applies curvature by forming arcuate vane platforms that follow the contour of the combustor liner panels, creating a smooth curved transition instead of sharp corners or flat surfaces. This curved geometry eliminates flow stagnation and bow wave effects, reducing thermal loads on the combustor liner panels and turbine vane leading edges, thereby improving durability without significantly increasing structural complexity
Solution Approach 2:
The patent applies different geometric characteristics to different regions of the interface. The arcuate vane platforms are designed to specifically follow the contour of the combustor liner panels in the critical flow path regions, while other portions of the structure maintain conventional geometries. This localized application of curved surfaces targets the specific areas experiencing flow stagnation and thermal loading, improving reliability without requiring complete redesign of the entire interface
2Object-affected harmful factors
If the vane platforms are designed to follow the combustor liner panel contours, then flow stagnation and thermal loads are reduced, but manufacturing complexity increases
Solution Approach 1:
The arcuate vane platforms are designed with curved surfaces that follow the combustor liner panel contours. While curved surfaces can be more challenging to manufacture than flat surfaces, the patent specifies that these curves are formed by extending the existing liner panel contours, which are already part of the combustor structure. This approach leverages existing manufacturing processes and tooling, reducing the additional complexity compared to creating entirely new curved geometries
3Use of energy by stationary object
If a smooth flow path is created by extending liner panel contours, then cooling requirements are reduced, but design complexity increases
Solution Approach 1:
The patent merges the flow path geometry with the existing combustor liner panel structure by extending the liner panel contours to form the vane platforms. This integration ensures that the smooth flow path is achieved without adding separate cooling systems or complex thermal management components. The same structural elements that form the combustor liner also define the turbine interface geometry, reducing overall design complexity while maintaining effective cooling
Solution Approach 2:
The curved geometry of the vane platforms following the liner panel contours creates a smooth flow path that reduces thermal loading on components. This curved design is achieved by extending the existing liner panel contours, which are already designed with specific curvature to manage flow and thermal fields. By reusing this pre-designed curvature, the patent avoids the need for additional complex cooling systems
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 reduces cooling requirements, enhances durability by minimizing thermal loads on combustor and turbine components, and prevents oxidation, thereby improving the overall performance and longevity of the engine.
Implementation Method 1
The arcuate outer vane platform includes a segment along the axis which follows the outer combustor liner panel structure and the arcuate inner vane platform includes a segment which follows the inner combustor liner panel structure to define a smooth flow path from the combustor section into the turbine section
Implementation Method 2
effusion cooling to reduce thermal loads and secondary flow effects
Data Source
AI summary
A turbine vane downstream of a combustor section includes an arcuate outer vane platform defined about an axis, the arcuate outer vane platform includes a segment of the arcuate outer vane platform along the axis which follows an outer combustor liner panel structure and an arcuate inner vane platform defined about the axis, the arcuate inner vane platform includes a segment of the arcuate inner vane platform along the axis which follows an inner combustor liner panel structure.