Adaptive Segment Seal Structure for Hot Gas Intrusion Control
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Solution Overview
Problem
Traditional sealing methods, such as o-ring or packing seals, are ineffective in highly dynamic environments like aircraft and missile propulsion systems, where asymmetric radial and axial displacements occur, allowing invasive thermal energy and corrosive airflow to compromise internal hardware survivability.
Innovation Solution
A seal system with two layers of independently flexible segments, circumferentially offset to create a tortuous path for airflow, paired with an insulating member to provide additional cooling, effectively maintaining contact during significant displacements and limiting thermal and corrosive intrusion.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If traditional sealing methods (o-ring or packing seals) are used, then the sealing structure is simple, but the seal becomes ineffective under asymmetric radial and axial displacements, allowing thermal energy and corrosive airflow to compromise internal hardware
Solution Approach 1:
The seal is divided into multiple independently flexible segments arranged circumferentially around the longitudinal axis. Each segment can deflect independently to accommodate asymmetric radial and axial displacements between the engine nozzle and airframe, maintaining sealing contact where traditional unified seals fail under dynamic loading conditions
Solution Approach 2:
The seal transitions from a static traditional design to a dynamic structure where each segment can independently deflect and adapt to changing displacement conditions. This dynamic flexibility allows the seal to maintain effectiveness throughout the range of asymmetric radial and axial displacements experienced during propulsion system operation
2Object-affected harmful factors
If a single-layer seal is used, then the structure is simpler, but the seal allows direct airflow paths that reduce thermal energy inhibition effectiveness
Solution Approach 1:
The seal transitions from a single-layer two-dimensional structure to a multi-layer three-dimensional structure with circumferential offset. This dimensional addition creates overlapping segments and offset spaces between layers, forcing airflow into a tortuous three-dimensional path that significantly reduces thermal energy intrusion compared to direct flow through a single layer
Solution Approach 2:
The multi-layer seal divides the sealing function across multiple layers with circumferential offsets, where each layer's segments create staggered spaces. This segmentation forces airflow to navigate through offset spaces between layers rather than direct paths, enhancing thermal inhibition through a tortuous flow path
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 seal system effectively limits invasive thermal energy and corrosive airflow, maintaining contact under high deformation conditions and enhancing component survivability in dynamic environments, applicable to various aircraft and missile systems.
Implementation Method 1
each of the plurality of segments is independently flexible and configured to deflect independently of the other segments to accommodate radial and axial displacement
Implementation Method 2
the seal creates a non-direct or tortuous path for airflow therethrough
Implementation Method 3
The insulating member may provide an additional cooling effect on any air that may pass through the seal into an internal space of the aircraft from an external environment
Data Source
AI summary
A highly adaptive seal for use in advanced aircraft propulsion and missile systems is provided. The seal is capable of effectively limiting invasive thermal energy and corrosive airflow from entering the internal systems and hardware of the aircraft by managing and controlling the incoming air flow. The seal is configured to be disposed between component parts of the aircraft and create a tortuous path for air flow. The seal maintains contact with the component parts between which it seals by allowing for significant radial and axial displacement freedom of the component parts. Accordingly, hot gas intrusion may be limited in a wide variety of dynamic environments and component displacement conditions. Limiting such hot gas intrusion has a substantial impact on component survivability over the course of free flight of an aircraft.