Diffuser-Turbine Flow Network Using Suction and Film Cooling
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Solution Overview
Problem
Existing gas turbine engines, particularly attritable engines, experience significant flow separation in the compressor diffuser airfoil section, which negatively impacts performance, and post-processing of diffuser vanes is challenging due to additive manufacturing limitations.
Innovation Solution
A compressor diffuser vane and turbine nozzle vane flow network is designed with suction points, suction flow passages, a main artery, and film holes to prevent flow separation and enhance cooling, utilizing air to maintain flow attachment and remove thermal energy.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If additive manufacturing is used to create a unitized engine configuration, then manufacturing complexity is reduced and production efficiency is improved, but post-processing of diffuser vanes becomes extremely challenging
Solution Approach 1:
The diffuser vane is segmented into multiple functional zones with embedded flow control features (suction points, suction flow passages, film holes, and cooling passages) that are integrated into the additive manufacturing process, eliminating the need for complex post-processing operations
2Ease of manufacture
If traditional diffuser vane design is used, then manufacturing is simpler, but significant flow separation occurs in the compressor diffuser airfoil section negatively impacting performance
Solution Approach 1:
The flow control features (suction points and cooling passages) are pre-designed and integrated into the diffuser vane structure during additive manufacturing, preventing flow separation before it occurs rather than attempting to correct it afterward
Solution Approach 2:
The invention uses fluid dynamics principles by implementing suction flow passages that draw fluid toward suction points on the diffuser vane surface, and cooling passages that manage thermal flows, to control and maintain attached flow in the compressor diffuser section
3Reliability
If diffuser vanes are designed with flow control features, then flow separation is prevented and performance is improved, but the device complexity increases
Solution Approach 1:
Multiple flow control functions (suction points, suction flow passages, film holes, and cooling passages) are merged and integrated into a single diffuser vane structure, allowing complex flow control to be achieved without proportionally increasing overall device complexity
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 flow network prevents flow separation and improves turbine vane cooling, leading to enhanced engine efficiency, increased turbine inlet temperatures, and extended vane life.
Implementation Method 1
a suction flow passage fluidly coupled to the at least one suction point
Implementation Method 2
air flowing within the main artery removes thermal energy from the turbine nozzle vane, the thermal energy being produced from exposure to hot gases flowing across the turbine nozzle vane
Implementation Method 3
the at least one film hole being configured to produce a film layer over the inner platform providing an insulating protective function from hot gases flowing toward a turbine section
Data Source
AI summary
A compressor diffuser vane and turbine nozzle vane flow network including at least one suction point formed in a suction side of the compressor diffuser vane; a suction flow passage fluidly coupled to the at least one suction point; a main artery formed within an outer platform, the outer platform in operative communication with the compressor diffuser vane, the main artery formed within the turbine nozzle vane, the turbine nozzle vane in operative communication with the outer platform, the main artery formed within an inner platform, the inner platform in operative communication with the turbine nozzle vane; film hole passages fluidly coupled to the main artery; and at least one film hole formed in the inner platform, the at least one film hole fluidly coupled to the main artery.