Variable Area Inlet Axial Translation for Mass Flow Control
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Solution Overview
Problem
Existing aircraft propulsion systems with variable airflow inlet areas face challenges in adapting to changing mass flow requirements during different flight conditions, such as supersonic and subsonic speeds, necessitating an improved inlet assembly that can dynamically adjust airflow.
Innovation Solution
The aircraft propulsion system incorporates a variable area inlet with a center body, aft fixed structure, and forward moveable structure, which form an annular inner airflow passage and secondary outer airflow passages, allowing for axial translation to adjust airflow and regulate mass flow, thereby accommodating varying operational conditions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If a fixed inlet structure is used, then the structure is simple and reliable, but the mass flow cannot be adjusted for different flight conditions
Solution Approach 1:
The inlet structure incorporates a moveable forward section that can translate axially between different positions to dynamically adjust the inlet area. This allows the mass flow to be adapted for different flight conditions (supersonic and subsonic) while maintaining a relatively simple overall structure based on a fixed center body and aft section.
2Quantity of substance
If the inlet area is increased for supersonic flight, then more mass flow is available, but the inlet area must be reduced for subsonic flight to optimize performance
Solution Approach 1:
The forward moveable structure translates axially to increase the inlet area when supersonic flight is detected, allowing greater mass flow. When subsonic flight conditions are detected, the structure retracts to reduce the inlet area, optimizing performance for different flight regimes.
Solution Approach 2:
The system changes the physical parameter of inlet area by translating the forward moveable structure to different axial positions, thereby adapting the mass flow capacity to match the detected flight conditions (supersonic or subsonic).
Data Source
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AI summary
An assembly is provided for an aircraft propulsion system (20). This assembly includes a variable area inlet (66). The variable area inlet (66) includes a moveable structure (72) configured to move axially along an axial centerline (30, 78) between a first position and a second position. The variable area inlet (66) is configured to open an airflow inlet passage (74) into the aircraft propulsion system (20) when the movable structure (72) is in the first position. The variable area inlet (66) is configured to close the airflow inlet passage (74) when the movable structure (72) is in the second position. The airflow inlet passage (74) includes an inlet. The inlet extends axially along the axial centerline (30, 78) from a first end to a second end. A distance from the first end to the second end changes as the inlet extends laterally between a first side (138) and a second side (140).