Gas Turbine Inducer Assembly Contoured Discharge Regions
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Solution Overview
Problem
The efficiency of cooling systems in gas turbine engines is limited by the structure and interaction of certain components, which restricts the ability to achieve lower cooling temperatures, impacting the engine's performance and efficiency.
Innovation Solution
A fluid flow inducer assembly with contoured shaped discharge regions that generates high swirl with a reduced pressure drop, turning fluid flow in a substantially circumferential direction into an exit cavity, minimizing mixing losses and enhancing efficiency by guiding fluid flows effectively.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If conventional cooling system structure is used, then the system is simple to manufacture, but the cooling temperature cannot be reduced sufficiently
Solution Approach 1:
The inducer assembly employs contoured discharge regions with curved surfaces instead of straight or angular geometries. The contoured shape of the discharge regions creates optimized flow paths that enhance swirl generation and improve cooling effectiveness, resolving the contradiction between achieving lower temperatures and maintaining manufacturing simplicity.
Solution Approach 2:
The invention modifies the geometric parameters of the cooling system by introducing contoured discharge regions with specific curvature radii and angles. These parameter changes optimize the fluid dynamics within the cooling passages, enabling lower cooling temperatures while the contoured design remains manufacturable using standard aerospace manufacturing processes.
2Productivity
If contoured discharge regions are used to generate high swirl, then cooling efficiency improves, but device complexity increases
Solution Approach 1:
The contoured discharge regions serve multiple functions simultaneously: they generate high swirl, guide fluid flow, and define cooling passages. By integrating these functions into a single contoured structure rather than using separate components, the invention improves cooling efficiency while minimizing the increase in device complexity.
Solution Approach 2:
The contoured discharge regions use curved geometries to achieve multiple objectives: the curvature generates swirl, directs flow paths, and defines passage boundaries. This multi-functional curvature approach enhances cooling efficiency without requiring additional complex components, as the same contoured surfaces perform multiple roles in the fluid flow management.
3Loss of energy
If conventional flow passages are used, then the structure is simple, but mixing losses are high
Solution Approach 1:
The contoured flow passages use curved surfaces to guide fluid flow smoothly through the inducer assembly. The contoured geometry reduces flow separation and minimizes mixing losses by creating more gradual flow transitions, resolving the contradiction between reducing energy losses and maintaining structural simplicity.
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 increased efficiency of the inducer assembly results in more cavity swirl and lower relative temperatures for the cooling fluid flow, reducing flow requirements for turbine blades, improving blade life, and enhancing the overall performance of the gas turbine engine.
Implementation Method 1
The inducer assembly is configured to receive a fluid flow from a compressor fluid source and to turn the fluid flow in a substantially circumferential direction into the exit cavity
Implementation Method 2
The first surface is configured to guide a cavity fluid flow away from the fluid flow exiting from the outlet
Implementation Method 3
Gas turbine engines typically include cooling systems (e.g., inducer) which provide cooling air to turbine rotor components, such as turbine blades, in order to limit the temperatures experienced by such components
Data Source
AI summary
A system includes an inducer assembly configured to receive a fluid flow from compressor fluid source and to turn the fluid flow in a substantially circumferential direction into the exit cavity. The inducer assembly includes multiple flow passages. Each flow passage includes an inlet configured to receive the fluid flow and an outlet configured to discharge the fluid flow into the exit cavity, and each flow passage is defined by a first wall portion and a second wall portion extending between the inlet and the outlet. The first wall portion includes a first surface adjacent the outlet that extends into the exit cavity.