Gas Turbine Diffuser Flow Splitter for Vane Cooling
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Solution Overview
Problem
In gas turbine engines, the increased bypass ratio and high pressure at the exit of the high-pressure compressor lead to local pressure drops and durability issues due to hot spots in the turbine section, affecting the diffuser flow and vane cooling efficiency.
Innovation Solution
A diffuser flow splitter system, comprising an annular ring and flow splitter components, is used to split the diffuser flow into radially spaced cavities, providing efficient cooling and minimizing pressure drops by directing air to specific areas, including a tangential on-board injector for the turbine rotor, and a ring seal to secure the turbine vane.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If air is pulled from large bosses on the diffuser case for cooling, then cooling is provided, but local pressure drops occur that affect dilution effectiveness and vane cooling
Solution Approach 1:
The diffuser flow is segmented into multiple separate flows using a flow splitter. The splitter divides the single diffuser flow into at least a first flow and a second flow, directing them to different destinations (vane cooling and dilution). This segmentation prevents the harmful interaction where one flow steals pressure from the other, allowing each flow to maintain its required pressure and effectiveness independently.
2Quantity of substance
If the bypass ratio is increased, then the volume of air delivered into the bypass duct increases, but the efficiency of utilizing compressed air in the compressor section decreases
Solution Approach 1:
The diffuser flow is made multi-functional by splitting it to serve multiple purposes simultaneously. The first flow provides vane cooling while the second flow provides dilution air for the combustor. This allows the engine to effectively utilize the compressed air from the compressor section for both cooling and combustion support functions, improving overall air utilization efficiency despite the high bypass ratio.
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 enhances the pattern factor and durability of the turbine section by evenly distributing the diffuser flow, reducing local pressure drops and improving vane cooling, thus increasing the efficiency and reliability of the gas turbine engine.
Implementation Method 1
A diffuser flow splitter system, comprising an annular ring and flow splitter components, is used to split the diffuser flow into radially spaced cavities
Implementation Method 2
providing efficient cooling and minimizing pressure drops by directing air to specific areas, including a tangential on-board injector for the turbine rotor
Data Source
Figure 1
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AI summary
A gas turbine engine includes an engine static structure that has a fluid port. A turbine vane is supported relative to the engine static structure and includes a cooling passage. A flow splitter is provided between the engine static structure and the turbine vane. The flow splitter is configured to divide a flow upstream from the flow splitter into a first fluid flow provided to the fluid port and a second fluid flow provided to the cooling passage.