Gas Turbine Nozzle Offset Corner Thermal Resilience
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Solution Overview
Problem
Current gas turbine nozzle components are not adequately designed to withstand high operating temperatures, leading to potential performance and efficiency issues due to inadequate thermal management.
Innovation Solution
A gas turbine nozzle assembly with an offset corner structure and stress relief pockets is introduced, featuring an airfoil-shaped cross section with offset flow surfaces and constant fillets to minimize aerodynamic contour changes and optimize the gas path gap between the nozzle and adjoining bucket, thereby enhancing thermal resilience and efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If current nozzle platform designs are used, then manufacturing is simpler, but thermal resilience and ability to withstand high operating temperatures deteriorates
Solution Approach 1:
The platform corner is segmented into multiple surfaces (first corner surface, second corner surface, third corner surface) with different orientations and functions. This segmentation allows each surface to be optimized for specific thermal and aerodynamic requirements while maintaining overall structural integrity
Solution Approach 2:
Different regions of the platform corner are given different geometric properties and orientations. The first corner surface has a specific orientation for thermal management, the second corner surface optimizes aerodynamic flow, and the third corner surface maintains structural support. This local optimization enables the platform to withstand high temperatures while maintaining aerodynamic efficiency
2Productivity
If conventional platform designs are used, then manufacturing is less complex, but aerodynamic efficiency and gas path gap optimization deteriorates
Solution Approach 1:
The platform corner design extends into multiple spatial dimensions with surfaces oriented at different angles and positions. This multi-dimensional approach allows optimization of gas path gaps and aerodynamic flow in three-dimensional space, improving turbine efficiency by better controlling the combustion gas flow path
Solution Approach 2:
The multiple corner surfaces are nested within each other in a hierarchical arrangement, with the first, second, and third corner surfaces creating nested flow paths. This nested structure efficiently manages the complex three-dimensional flow of combustion gas while maintaining a relatively compact overall platform structure
3Manufacturing precision
If simple platform designs are used, then manufacturing is less expensive, but ability to maintain gas path gap and minimize aerodynamic contour changes deteriorates
Solution Approach 1:
The platform corner employs asymmetric surface orientations where the first, second, and third corner surfaces are angled differently relative to each other and the platform centerline. This asymmetric design allows precise control of the gas path gap between adjacent nozzles while minimizing aerodynamic contour changes, achieving high manufacturing precision in the gas path geometry
Data Source
AI summary
A gas turbine nozzle assembly of a gas turbine is provided. The turbine nozzle assembly may include a turbine nozzle extending from an inner platform to an outer platform and having an airfoil-shaped cross section having a leading edge and a trailing edge, and a pressure side and a suction side each of which extends from the leading edge to the trailing edge, wherein the turbine nozzle may include a plurality of vanes attached to the inner and outer platforms and the inner platform having an attached first and second endfaces and a flow surface surrounding opposing ends of a vane of the plurality of vanes, the flow surface terminating circumferentially at the first and second endfaces and terminating axially at forward and aft edges, and the inner platform may include a platform corner portion comprising the flow surface attached to the first endface at the forward edge and attached to the second endface at the aft edge.