Fluidic Thrust Vectoring Nozzle With Disturbance Generator
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Solution Overview
Problem
Existing thrust vectoring systems for jet engine nozzles face challenges such as weight penalties from mechanical systems, high flow requirements in fluidic systems, and thrust losses due to shock wave generation, which affect maneuverability and performance.
Innovation Solution
A convergent-divergent nozzle design with a sharp throat and a disturbance generator that induces shockless flow separation on the divergent wall, allowing for efficient thrust vectoring with reduced flow injection and minimal thrust loss, using a convergent inlet portion and a divergent outlet portion with a total angle less than 150 degrees and a divergence angle of at least 12 degrees, along with injection flow slots strategically located to create a flow separation zone extending from the throat to the nozzle trailing edge.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If mechanical deflecting surfaces or gimballing of the entire nozzle are used for thrust vectoring, then aerodynamic control is achieved, but weight increases due to large control surfaces and actuators
Solution Approach 1:
The patent replaces mechanical thrust vectoring systems (deflecting surfaces, actuators) with a fluidic system that uses flow injection to generate shock waves and alter flow direction. This substitution eliminates heavy mechanical components while achieving the same aerodynamic control function through fluid dynamics
Solution Approach 2:
The invention uses fluidic injection (pneumatics) to create shock waves in the supersonic flow within the divergent section of the nozzle. By injecting flow at specific locations and angles, the system generates oblique shock waves that turn the main flow asymmetrically, achieving thrust vectoring without mechanical moving parts
2Ease of operation
If large amounts of flow are injected into the divergent section to generate strong shock waves for shock vectoring, then flow direction is altered, but engine performance deteriorates due to loss of thrust-producing flow
Solution Approach 1:
The patent optimizes multiple parameters of the injection system including injection location (in the divergent section), injection angle (oblique to the flow direction), injection flow rate, and nozzle geometry (divergence angle). By carefully adjusting these parameters, the system generates sufficient shock wave strength for effective vectoring while minimizing the amount of injected flow and preserving engine performance
3Ease of operation
If sonic line skewing is achieved by injecting flow near the throat to direct flow at an angle, then thrust vectoring is obtained, but intricate nozzle inner mold line shaping is required to maintain constant mass flow
Solution Approach 1:
The patent extracts the vectoring function from the nozzle throat region and relocates it to the divergent section. By injecting flow in the divergent section rather than near the throat, the system avoids the need for complex throat shaping while achieving effective thrust vectoring through shock wave generation in the expanded flow field
4Ease of operation
If strong shock waves are created in the divergent section for shock vectoring, then flow direction is changed, but thrust is reduced
Solution Approach 1:
The patent optimizes the injection parameters (flow rate, angle, location) and nozzle geometry (divergence angle between 12-15 degrees) to generate shock waves of appropriate strength that achieve the desired flow direction change while minimizing thrust loss. The optimized parameters ensure the shock waves are strong enough for effective vectoring but not so strong as to cause excessive thrust reduction
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 design achieves effective thrust vectoring with lower flow injection, minimizing thrust losses and weight penalties, while maintaining engine mass flow and providing a simple, efficient fluidic vectoring solution.
Implementation Method 1
A disturbance generator is located to induce shockless flow separation on the divergent wall. The predetermined wall angle is sufficient for the induced flow separation to extend upstream from disturbance generator substantially to the throat of the nozzle.
Implementation Method 2
Shock vectoring schemes inject flow into the divergent section of the nozzle such that a shock wave is generated in the supersonic flow thereby turning the flow.
Implementation Method 3
a convergent-divergent nozzle with a convergent inlet portion, a divergent outlet portion and a sharp throat therebetween
Data Source
AI summary
A thrust vectoring system is created with a convergent-divergent nozzle having a total angle no greater than 150 degrees. A divergent portion of the nozzle has a wall at a predetermined angle of at least 12° from the freestream direction. A disturbance generator is located on the wall to induce flow separation from the wall with the predetermined wall angle sufficient for the induced flow separation to extend upstream from disturbance generator substantially to a throat of the nozzle pressurizing the wall and creating a net vector angle in jet flow through the nozzle.