Gas Turbine Casing Ring Assembly with Conduction Cut
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Solution Overview
Problem
Gas turbine compressor casings face challenges in maintaining desired radial clearances due to mismatched thermal growth characteristics between rotor and stator assemblies, especially in high-pressure regions where temperature variations affect operational efficiency.
Innovation Solution
A compressor casing assembly featuring a conduction cut structure between inner and outer rings, where the cavity is filled with a material having lower thermal conductivity than the rings, such as cellular materials or ceramics, to reduce the outer ring's temperature and slow down thermal response, thereby matching it with the rotor's thermal response.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If the casing is made as a monolithic structure with continuous heat flowpath, then structural strength is improved, but thermal response mismatch with rotor worsens
Solution Approach 1:
The casing is divided into inner ring and outer ring segments with a conduction cut between them. This segmentation interrupts the continuous heat flowpath while maintaining structural integrity through separate support mechanisms, allowing differential thermal expansion between the segments to match rotor thermal response characteristics.
Solution Approach 2:
The casing employs composite construction with inner ring, outer ring, and conduction cut structure forming a composite system. This composite structure enables tailored thermal and mechanical properties in different regions, providing both structural strength and controlled thermal response characteristics.
2Reliability
If the outer ring temperature is reduced to slow thermal response, then thermal response matching is improved, but heat dissipation efficiency worsens
Solution Approach 1:
The conduction cut structure is strategically positioned between the inner and outer rings to create localized thermal insulation where needed. This local modification reduces heat transfer to the outer ring specifically, slowing its thermal response without significantly impacting overall heat dissipation efficiency of the casing system.
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 solution effectively reduces the outer ring's temperature and slows down the casing's thermal response, improving the match with the rotor's thermal response, which helps maintain acceptable radial clearances and enhances operational efficiency.
Implementation Method 1
a conduction cut structure disposed between the inner and outer rings
Data Source
AI summary
A casing assembly for a gas turbine engine having a centerline axis, the casing apparatus includes: a metallic inner ring defining an annular flowpath surface; a metallic outer ring positioned in axial alignment with and radially outward of the inner ring; and a conduction cut structure disposed between the inner and outer rings.