Curved Seal Retainer Structure for Low-Distortion Turbine Flow
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Solution Overview
Problem
Gas turbine engine components, particularly igniter plugs, cause significant aerodynamic blockage and flow distortion due to bulky housings and sharp edges, negatively impacting downstream components and systems.
Innovation Solution
A seal structure comprising a seal element and retainer with specific curvature profiles and dimensions, connected to a supporting structure, minimizes flow perturbation by preventing separation bubbles and reducing wake dimensions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a bulky housing is used for the floating seal to accommodate relative movement, then the seal can effectively facilitate insertion and accommodate movement between combustor components, but the housing causes significant aerodynamic blockage and flow distortion within the outer annulus
Solution Approach 1:
The patent applies curvature to the external convex surface of the retainer, specifically defining a first peripheral curved portion with a first local radius ranging between 10% to 30% of the outer transversal diameter. This curved geometry eliminates sharp edges that cause flow separation and distortion, allowing the seal structure to maintain aerodynamic smoothness while still providing the necessary housing for the floating seal to accommodate relative movement between the combustor outer casing and flame tube.
2Ease of manufacture
If sharp edges are present on the housing to simplify manufacturing, then manufacturing is easier and costs are reduced, but the sharp edges exacerbate annulus flow distortions and negatively impact downstream components
Solution Approach 1:
The patent specifies that the external convex surface of the retainer includes a first peripheral curved portion defined by a first local radius ranging between 10% to 30% of the outer transversal diameter. This curvature requirement replaces sharp edges throughout the housing structure, eliminating flow separation points while maintaining manufacturability through defined geometric parameters that can be implemented using standard machining or forming processes.
3Reliability
If the retainer height is increased to provide sufficient engagement for the seal element, then the seal engagement is more secure, but the aerodynamic penalty and flow distortion increase
Solution Approach 1:
The patent defines specific parameter ranges to optimize the balance between seal engagement and aerodynamic performance. The height of the retainer is constrained to range between 25% to 40% of the outer transversal diameter, and the first local radius is defined as 10% to 30% of the outer transversal diameter. These parameter specifications ensure sufficient seal engagement while minimizing the aerodynamic penalty through optimized dimensional proportions.
Data Source
AI summary
A seal structure for a gas turbine engine. The seal structure comprises a seal element, a retainer having an outer transversal diameter along a transversal axis and engaging the seal element. The retainer is connected to a supporting structure and comprises an external upper surface having a central convex portion and a peripheral curved portion.