Gas Turbine Combustion Chamber Tile Support Structure
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Solution Overview
Problem
Existing supporting structures for gas turbine combustion chamber heat-insulating tiles face challenges in maintaining effective insulation and efficient assembly, particularly in toroidal chambers, where metallic inserts compromise insulation and require additional cooling systems, and specialized tiles are costly and not universally applicable.
Innovation Solution
A supporting structure comprising elastic metal connection elements with a clamping device and threaded pins allows for secure attachment of refractory tiles without holes, ensuring continuous insulation and simplified assembly, using pre-assembled modules that integrate with existing cooling systems.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If metallic tiles are used for the last position in each row to simplify assembly, then assembly ease is improved, but thermal insulation performance deteriorates
Solution Approach 1:
A refractory tile intermediary component is introduced between the metallic connection element and the combustion chamber environment. This intermediary tile maintains the thermal insulation function while allowing the metallic connection element to perform its fastening function, thus resolving the contradiction between assembly ease and thermal insulation performance.
Solution Approach 2:
The system is segmented into distinct functional components: metallic connection elements for assembly and refractory tiles for insulation. By separating these functions into different components, each can optimize its performance without compromising the other.
2Ease of operation
If perforated refractory tiles with metallic through screws are used, then assembly is simplified, but cooling system complexity increases due to exposed metallic parts
Solution Approach 1:
The refractory tile acts as an intermediary barrier that prevents direct exposure of metallic connection elements to the high-temperature combustion chamber environment. This eliminates the need for complex cooling systems for the metallic parts while maintaining assembly simplicity.
Solution Approach 2:
The metallic connection elements are extracted from the direct thermal environment and positioned behind the refractory tile barrier. This separation removes the thermal exposure issue while preserving the assembly advantages of metallic fasteners.
3Adaptability or versatility
If specialized perforated refractory tiles are manufactured for specific positions, then assembly flexibility is improved, but manufacturing cost increases
Solution Approach 1:
The connection element design is made universal and can be used in any position within the combustion chamber lining. The refractory tile intermediary component provides the necessary thermal barrier function regardless of position, eliminating the need for specialized perforated tiles and reducing manufacturing costs while maintaining assembly flexibility.
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 solution provides uniform, high-efficiency insulation with refractory tiles, reduces thermal energy losses, eliminates the need for costly specialized tiles, and simplifies assembly, while maintaining effective cooling without exposing metallic components to high temperatures.
Implementation Method 1
supporting structures (3) for fixing the heat-insulating tile (2) to the walls of a gas turbine combustion chamber
Implementation Method 2
the combustion chamber of gas turbines must be provided on the inside with a heat-insulating lining made of refractory material
Data Source
Figure 1~2
Figure 3~4
Figure 5
AI summary
A supporting structure for gas turbine combustion chamber heat-insulating tiles, includes: a first connection element and second connection element (5, 6) having respective first ends (5a, 6a), configured to fit onto sides of a heat-insulating tile (2) of a gas turbine combustion chamber (20), and respective second ends (5b, 6b); a clamping device (7); and a fixing device (8), provided with a threaded pin (15), extending from the clamping device (7) on the side opposite to the heat-insulating tile (2) in use, and with a nut (16). The connection elements (5, 6) clamped by the clamping device (7), and extend in opposite directions from the clamping device (7). The threaded pin (15) is rigidly connected to the clamping device (7), so as to prevent rotations of the threaded pin (15) with respect to the clamping device (7).