Gas Turbine Combustor Endcover Assembly with Integrated Flow Restrictor
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Solution Overview
Problem
Existing endcover assemblies for gas turbine combustors are complex and prone to leakage due to the use of multiple internal passages and brazed joints, which can crack, and require complicated assembly processes for flow restrictor inserts.
Innovation Solution
A simplified endcover assembly design featuring a flat plate with internal fuel passages and a fuel manifold porting block, where flow restrictor inserts with multiple orifices are secured between the plate and the porting block, providing a secure and leak-proof interface using bolts and counterbores for assembly.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If multiple internal passages and brazed joints are used in endcover assemblies, then the ability to accommodate multiple fuel nozzles is improved, but the complexity of construction increases and the risk of cracking rises
Solution Approach 1:
The endcover is divided into separate functional components: a flat plate portion for structural support and a porting block portion for fluid distribution. This segmentation allows each part to be optimized independently and assembled through simpler means, reducing overall construction complexity while maintaining the ability to support multiple nozzles
Solution Approach 2:
The complex internal passage network is extracted and relocated to the porting block portion, which is then separately assembled to the flat plate. This extraction eliminates the need for complex internal passages within the main endcover body, reducing construction complexity while preserving multi-nozzle capability
2Reliability
If brazed joints are used to seal extra parts including inserts in endcovers, then sealing capability is improved, but the risk of cracking increases
Solution Approach 1:
The sealing function is merged with the gasket that already exists between the endcover and combustion liner. The gasket is extended to seal around the flow restrictor inserts, eliminating the need for separate brazed joints for sealing while maintaining sealing capability
Solution Approach 2:
The flow restrictor inserts are extracted as separate components that are pressed into the flat plate, rather than being integrated into the endcover with brazed joints. This extraction eliminates the cracking-prone brazed joints while preserving the sealing function through the gasket
3Ease of manufacture
If flow restrictors are pressed and staked into place on the hot side of the endcover, then assembly is achieved, but leakage may occur and assembly complexity increases
Solution Approach 1:
Instead of pressing and staking flow restrictors into the hot side of the endcover, the invention inverts the approach by pressing them into the cold side (flat plate portion) and sealing them with the gasket on the hot side. This inversion simplifies assembly while improving sealing reliability
Solution Approach 2:
The gasket serves multiple functions: sealing between the endcover and combustion liner, and sealing around the flow restrictor inserts. This multi-functionality eliminates the need for separate sealing mechanisms, reducing assembly complexity while improving leakage prevention
Data Source
AI summary
An endcover assembly for a turbine combustor adapted to support one or more combustor nozzles includes a substantially flat plate having one side which in use, faces a combustion chamber and an opposite side which, in use, faces away from the combustion chamber. At least one fuel passage extends through the substantially flat plate. A fuel manifold porting block is secured to the opposite side of the flat plate with at least one port aligned with the at least one passage. A fuel restrictor insert formed with multiple flow orifices is located between the flat plate and the fuel manifold porting block in alignment with the at least one fuel passage and the at least one port.