Turbine nozzle and method for cooling a turbine nozzle of a gas turbine
The interlaced cooling passage design in turbine nozzles addresses complexity and cost issues by enhancing cooling efficiency and heat transfer, ensuring durability and improved gas turbine performance.
DE102014118697B4Active Publication Date: 2025-07-31GENERAL ELECTRIC TECH GMBH
Patent Information
- Application Number
- DE102014118697
- Authority / Receiving Office
- DE · DE
- Patent Type
- Patents
- Current Assignee / Owner
- Priority Date
- 2013-12-27
- Filing Date
- 2014-12-16
- Publication Date
- 2025-07-31
- Estimated Expiration
- 2034-12-16
AI Technical Summary
Technical Problem
Existing turbine nozzles face challenges in maximizing cooling coverage while minimizing manufacturing complexity, cost, and pressure drop, as well as optimizing heat transfer performance in high-temperature environments.
Method used
A turbine nozzle design featuring interlaced or overlapping first and second cooling passages that direct cooling fluid flows in opposite directions to enhance cooling efficiency, reduce complexity, and minimize pressure drop.
Benefits of technology
The design optimizes cooling channels to withstand high operating temperatures, reducing manufacturing costs and complexity while maintaining efficient heat transfer performance, thereby extending the nozzle's lifespan and improving gas turbine efficiency.
✦ Generated by Eureka AI based on patent content.
Smart Images
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Abstract
Turbine nozzle (80, 100, 200, 300, 400) for a gas turbine, the turbine nozzle (80, 100, 200, 300, 400) comprising:a first guide vane (102, 202, 302, 402);a second guide vane (104, 204, 304, 404); anda platform (106, 206, 306, 406) interconnecting the first vane (102, 202, 302, 402) and the second vane (104, 204, 304, 404), the platform (106, 206, 306, 406) having a first cooling channel (112, 212, 312, 412) and a separate second cooling channel (114, 214, 314, 414) defined therein;wherein the first cooling channel (112, 212, 312, 412) is configured to direct a first cooling fluid flow (132, 232, 332, 432) in a first direction; andwherein the second cooling channel (114, 214, 314, 414) is configured to direct a second cooling fluid flow (134, 234, 334, 434) in a second direction substantially opposite to the first direction;characterized in that the first cooling channel (212) and the second cooling channel (214) at least partially interlock; and / or the first cooling channel (112, 312, 412) and the second cooling channel (114, 314, 414) at least partially overlap each other in the axial direction or radial direction; and / or the first cooling channel (212, 412) and the second cooling channel (214, 414) are at least partially interlaced with each other.;
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Citation Information
Patent Citations
Gas turbine
JP1993052102A
JP0000H0552102A