Pre-Swirl Nozzle Carrier Inlet Geometry to Minimize Flow Separation
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Solution Overview
Problem
Pre-swirl nozzles in gas turbine engines experience flow separation at the inlet region, leading to reduced swirl and ineffective cooling of rotating components, which is not adequately addressed by existing bevel designs.
Innovation Solution
A pre-swirl nozzle carrier with a structured periphery featuring a combination of convex and concave curvatures at the inlet opening, designed to minimize flow separation and enhance swirl, along with an aerodynamically optimized inlet funnel for improved air introduction.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Manufacturing precision
If a pre-swirl nozzle has a simple inlet opening without structured periphery, then the manufacturing is simpler, but flow separation occurs in the inlet region reducing outlet velocity and swirl
Solution Approach 1:
The inlet opening periphery is designed with specific convex and concave curvatures instead of sharp edges or simple rounded forms. The convex curvature region adjacent to the flow passage and the concave curvature region create a structured profile that guides flow smoothly into the passage, preventing separation while maintaining manufacturing feasibility through precise geometric definition.
Solution Approach 2:
The periphery of the inlet opening is given different curvature characteristics at different locations: a convex curvature in the region adjacent to the flow passage and a concave curvature in another region. This local differentiation of geometric properties optimizes flow attachment specifically where needed without unnecessarily complicating the entire structure.
2Reliability
If bevels are provided in the inlet region to avoid sharp edges, then flow separation is reduced, but the outlet velocity and swirl are still not sufficient
Solution Approach 1:
Instead of using simple bevels or single-radius rounded edges, the invention employs a composite curvature profile with both convex and concave regions. This sophisticated curved geometry more effectively manages the flow transition into the passage, ensuring stable attachment and maximizing outlet velocity and swirl for improved cooling productivity.
Solution Approach 2:
The periphery geometry is defined by specific curvature parameters - the radius and orientation of the convex curvature region and the concave curvature region. By optimizing these geometric parameters, the flow attachment is enhanced beyond what simple bevels achieve, resulting in higher outlet velocity and swirl that directly improve cooling effectiveness.
3Ease of operation
If the periphery has only convex curvature, then the inlet is smooth, but flow separation still occurs downstream of the entrance
Solution Approach 1:
The combination of convex and concave curvatures creates a more sophisticated flow guidance profile. The convex region ensures smooth entry, while the subsequent concave region helps maintain flow attachment downstream by creating a favorable pressure gradient, preventing separation that would occur with convex curvature alone.
Solution Approach 2:
The structured periphery with alternating convex and concave curvatures provides continuous flow guidance through the inlet region. This continuous geometric structuring maintains flow attachment stability throughout the entrance zone, not just at the immediate inlet, ensuring reliable flow progression through the entire passage.
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 structured periphery and inlet funnel design increase swirl intensity, reducing the inlet temperature of rotor blades, thereby improving cooling efficiency, reducing cooling mass flow, and enhancing specific fuel consumption and reducing nitrogen oxide generation.
Implementation Method 1
Pre-swirl nozzles typically form a separation bubble downstream of the inlet region of the pre-swirl nozzle. Such a flow separation reduces the outlet velocity of the air at the exit of the pre-swirl nozzle.
Implementation Method 2
Pre-swirl nozzles serve for diverting cooling air into a rotational direction upstream of a rotating component, for example upstream of a rotating turbine disk, and in so doing imparting swirl to the cooling air.
Implementation Method 3
the front side of the wall is connected to an inlet funnel which protrudes from the front side of the wall and which surrounds the inlet opening of the flow passage
Data Source
AI summary
A pre-swirl nozzle carrier for a gas turbine engine, includes: a wall having front and rear sides, and a multiplicity of pre-swirl nozzles formed in the wall and which each have a flow passage, wherein the flow passage has an inlet opening at the front side and an outlet opening at the rear side. The flow passages are provided and designed to discharge air, which has flowed in via the inlet opening, with swirl from the outlet opening. It is provided that the inlet opening is surrounded by a periphery which, at least in certain sections, has a region with a convex curvature adjacent to the flow passage and has a region with a concave curvature adjacent to said region with a convex curvature. The invention furthermore relates to a method for producing a pre-swirl nozzle in a pre-swirl nozzle carrier.


