Turbine Compressor Diffuser Splitter Flow Division
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Solution Overview
Problem
Current gas turbine compressor diffusers experience significant flow energy losses downstream of the compressor, which are mitigated by traditional controls that increase mechanical complexity and product costs, and multi-passage diffusers require extensive and costly casting and machining operations.
Innovation Solution
A diffuser design for a turbine engine that splits the compressor discharge air flow into secondary paths using a ring and splitter portion, supported by struts, allowing for efficient flow management and combustor assembly support, reducing the need for extensive machining and casting.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Loss of energy
If traditional controls are used to mitigate flow energy losses, then flow energy losses are reduced, but mechanical complexity and product costs increase
Solution Approach 1:
The patent combines the diffuser and combustor support functions into a single integrated component structure. The diffuser includes a body with an inner surface defining a passage and an outer surface, while combustor supports are integrated as part of this same structure rather than being separate components. This merging reduces the number of parts and mechanical complexity while maintaining the ability to mitigate flow energy losses through the diffuser passage design.
2Productivity
If multi-passage diffusers are used to manage flow, then flow management efficiency is improved, but casting and machining operations become extensive and costly
Solution Approach 1:
The diffuser passage is divided into multiple sections along its length, with each section having a different diffusion angle. The first section has a first diffusion angle, the second section has a second diffusion angle, and the third section has a third diffusion angle. This segmentation allows optimized flow management in each section while keeping the overall structure manufacturable through standard casting and machining processes, avoiding the need for complex multi-passage designs.
3Loss of energy
If the diffuser passage is divided into multiple sections with different diffusion angles, then flow energy losses are reduced, but manufacturing precision requirements increase
Solution Approach 1:
Different sections of the diffuser passage are assigned different diffusion angles optimized for their specific location and flow conditions. The first section has a first diffusion angle, the second section has a second diffusion angle, and the third section has a third diffusion angle. This local quality approach allows each section to be optimized for minimizing flow energy losses at that particular location, while the gradual changes between sections make the manufacturing precision requirements more manageable compared to abrupt transitions.
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 diffuser design effectively manages flow energy losses while minimizing mechanical complexity and product costs by integrating the splitter and ring portions with precise machining, enabling efficient support for combustor assemblies and reducing the need for extensive machining operations.
Implementation Method 1
The lead edge 70 is formed at an intersection of first and second forward faces 71 and 72 of the splitter portion body 61. The faces 71 and 72 are tapered toward one another in the upstream flow direction.
Data Source
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AI summary
A diffuser (10) for a turbine engine (91), including an annular casing (20) to seal compressor discharge air and struts (30) attached to the casing (20) to delimit an annular array of intra-strut regions (40), is provided and includes a ring portion (50), including a ring shaped annular body (51) with a forward face (53) disposed on a forward side thereof, the ring portion (50) being supportable by one or more of the struts (30), and a splitter portion (60), including a ring shaped annular body (61) with an aft face (62) disposed on an aft side thereof to mate with the forward face (53) of the ring portion body (51), the splitter portion (60) further including a lead edge (70), on a forward side of the splitter portion body (61), which is extendable into a flow path (80) of the compressor discharge air to split the flow path (80) into secondary flow paths (81, 82) defined radially outside of and inside of the splitter portion body (61).