DTSA Engine Inlet Airflow Modulator for Cooling and Cycle Matching
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Solution Overview
Problem
Supersonic aircraft face challenges with high temperatures due to propulsion systems, requiring engine cooling, but existing systems use external apertures that increase complexity, weight, and cost, and variable geometry intakes add weight and complexity while causing performance penalties at off-design conditions.
Innovation Solution
A decoupled third stream inlet duct system in a DTSA aircraft gas turbine engine modulates intake airflow using existing engine inlet geometry, eliminating the need for external apertures and mechanical systems, and adjusts airflow based on flight parameters to match engine requirements, providing efficient cooling and cycle matching.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If external apertures are used for engine bay cooling, then cooling airflow is provided to the engine bay, but aircraft complexity, weight, and cost increase
Solution Approach 1:
The existing inlet duct structure is made multi-functional by adding a movable modulator member that can redirect airflow between two functions: powering the DTSA turbine and cooling the engine bay. This eliminates the need for separate dedicated cooling apertures and systems, as the same inlet structure serves both purposes through dynamic flow modulation.
2Adaptability or versatility
If variable geometry intakes are used for cycle matching, then airflow intake is varied to match engine requirements, but weight and complexity increase
Solution Approach 1:
A movable modulator member is introduced into the inlet duct that can dynamically adjust its position to vary airflow distribution between the DTSA turbine and engine bay cooling. This dynamic adjustment capability enables cycle matching across different flight conditions without requiring complex variable geometry intake structures, achieving adaptability through a single movable component rather than multiple geometric variations.
3Device complexity
If fixed geometry intake systems are used, then weight and complexity are reduced, but performance penalties occur at off-design conditions
Solution Approach 1:
The inlet system performs self-adjustment through the movable modulator member that automatically varies airflow distribution based on operating conditions. This enables the fixed geometry intake to adapt its flow characteristics without external control systems or complex mechanisms, maintaining high efficiency across off-design conditions while preserving the simplicity and low weight of fixed geometry structures.
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
This solution reduces weight and complexity, enhances low observable signature, and improves airflow matching, reducing drag and performance penalties at off-design conditions by using existing engine geometry for airflow modulation and cooling, while maintaining efficient engine operation across varying flight conditions.
Implementation Method 1
utilizes the structure of a decoupled third stream inlet duct on a decoupled third stream annulus to modulate intake airflow between the inlet decoupled inlet duct and an engine bay cooling stream
Implementation Method 2
Supersonic aircraft endure extreme high temperatures caused by propulsion systems and in-flight engine cooling is required
Data Source
AI summary
The present invention relates to a system and method of LO airflow modulation for use with a DTSA engine. A DTSA engine is positioned within an aircraft fuselage and the second DTSA turbine fan includes it own dedicated decoupled air inlet duct that is formed co-centrically about the housing. An airflow modulator member is positioned in duct to form the duct wall when the modulator is in a closed position. The Modulator member is pivotally connected to the duct wall, and is movable by an actuator to a second open position that allows airflow to escape the third stream duct, and provide airflow to both the DTSA fan blades as well as engine bay for cooling. The method of the present invention provides airflow modulation to an aircraft employing a DTSA engine, said method including the receiving of airflow from a supersonic aircraft intake; sensing a number of parameters, including, but not limited to aircraft speed, temperature, engine load and/or altitude. Calculating an efficient amount of airflow to provide to the DTSA turbine blades thorough a decoupled airstream; and directing movement of a modulator vane located in the intake duct to vary airflow to the DTSA turbine.