Gas Turbine First Stage Vane Cooling Arrangement
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Solution Overview
Problem
Existing gas turbine first stage vane arrangements face challenges with inefficient cooling due to leakage and high cooling gas consumption, leading to power losses and emissions, as well as thermoacoustic issues between combustor cans.
Innovation Solution
The proposed first stage vane arrangement features extended and non-extended vanes with overlapping frame segments, where the leading section of extended vanes protects the I-beam from hot gases, reducing the need for cooling air and guiding it to cool the frame segments, while non-extended vanes directly cool exposed areas, minimizing thermoacoustic communication.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If sealed slots are used to allow movement between transition piece and support frame, then movement is enabled, but large amounts of cooling gas are lost due to ineffective sealing and uncontrolled leakage
Solution Approach 1:
The support frame is divided into multiple frame segments that can move independently relative to the transition piece. Each segment is separated by gaps that allow thermal expansion and movement while maintaining controlled cooling gas flow paths, preventing uncontrolled leakage through sealed slots.
Solution Approach 2:
Cooling gas serves as an intermediary substance that fills the gaps between frame segments and transition pieces. Instead of sealing these gaps, the cooling gas pressure controls the interface, allowing movement while preventing harmful leakage and providing simultaneous cooling function.
2Loss of energy
If frame segments are positioned close to vanes, then cooling efficiency improves, but thermoacoustic communication between combustor cans increases
Solution Approach 1:
The support frame is segmented into multiple independent frame segments positioned at different radial locations. This segmentation creates acoustic isolation between adjacent combustor cans, blocking thermoacoustic communication paths while maintaining effective cooling coverage through the distributed segment arrangement.
Solution Approach 2:
Frame segments are positioned asymmetrically with respect to the vanes, with varying gaps and distances from different vane leading edges. This asymmetric arrangement optimizes cooling coverage for each vane while strategically placing segments to interrupt acoustic wave paths between combustors, reducing thermoacoustic coupling.
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 the total amount of cooling fluid required, decreases power and efficiency losses, and minimizes emissions by optimizing cooling air distribution and reducing thermoacoustic interactions between combustor cans.
Implementation Method 1
the leading section of extended vanes protects the I-beam from hot gases
Implementation Method 2
guiding it to cool the frame segments
Data Source
AI summary
A first stage vane arrangement having an array of first stage vanes and an array of frame segments and method for cooling frame segments of the first vane arrangement of a gas turbine are disclosed. The frame segments are designed for axially receiving aft ends of a combustor transition pieces. The first stage vanes include extended vanes, each vane having a leading section, a trailing edge, and an airfoil extending between an outer platform and an inner platform. The frame segments having an I-beam with an upper horizontal element, a lower horizontal element, and a vertical web. The vertical web having a downstream face facing towards a first stage of a turbine when installed in a gas turbine. The downstream face of the vertical web of at least one of the frame segments overlaps, at least partially, the leading section of at least one of the extended vanes.