Exhaust Nozzle Transitioning Circular Inlet to Rectangular Exit
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing exhaust nozzle designs struggle to achieve combined monotonic pitch and yaw vectoring in three-dimensional configurations, as they tend to vector exhaust jets only in orthogonal directions defined by the nozzle exit shape, particularly when transitioning from a circular or elliptical inlet to a rectangular exit.
Innovation Solution
A three-dimensional exhaust nozzle design that transitions from a circular or elliptical inlet to a rectangular exit through an expansion and contraction region, using a smooth, curved surface geometry and tessellated panels to avoid corner formation, allowing for a gradual change in cross-sectional shape and enabling dual-axis vectoring.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If a three-dimensional exhaust nozzle transitions from circular inlet to rectangular exit, then the nozzle can achieve better thrust vectoring capability, but the nozzle structure becomes more complex and manufacturing difficulty increases
Solution Approach 1:
The nozzle is divided into multiple sections: a circular inlet section, a transition section with tessellated panels, and a rectangular exit section. This segmentation allows each section to be optimized independently while maintaining overall thrust vectoring capability, resolving the contradiction between versatility and complexity.
Solution Approach 2:
The transition section uses curved surface geometry with tessellated panels that smoothly connect the circular inlet to the rectangular exit. This curved transition avoids sharp corners while achieving the desired shape transformation, maintaining manufacturing feasibility while enabling enhanced thrust vectoring.
2Ease of manufacture
If sharp corners are used in the nozzle exit, then manufacturing is simpler, but thrust vectoring efficiency is reduced due to flow separation and premature turning
Solution Approach 1:
The nozzle exit uses rounded corners and curved surfaces instead of sharp angles. This curvature prevents flow separation and eliminates premature jet turning, significantly improving thrust vectoring efficiency while the curves are designed to be manufacturable using standard fabrication techniques.
Solution Approach 2:
The corner radius and surface curvature parameters are optimized to balance manufacturing ease with aerodynamic performance. By carefully selecting these geometric parameters, the design achieves high thrust vectoring efficiency without requiring excessively complex manufacturing processes.
3Device complexity
If orthogonal vectoring directions are used in rectangular nozzles, then the nozzle structure is simpler, but the ability to achieve combined pitch and yaw vectoring is limited
Solution Approach 1:
The nozzle design incorporates a third dimension in the transition section using tessellated panels that create a smooth three-dimensional surface. This 3D transition geometry enables the exhaust jet to vector simultaneously in pitch and yaw directions, achieving combined vectoring capability while keeping the overall structure manageable.
Solution Approach 2:
The transition section employs asymmetric tessellated panel arrangements that gradually transform the circular cross-section into a rectangular one. This asymmetric transition geometry creates the necessary flow conditions for combined pitch and yaw vectoring without requiring a fully complex nozzle structure.
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 enhances thrust vectoring efficiency by allowing up to 15 degrees of combined pitch/yaw vectoring in the 45-degree plane, improving propulsive efficiency and vectoring effectiveness compared to nozzles with sharp corners or orthogonal vectoring limitations.
Implementation Method 1
an elongate channel for directing exhaust gasses
Implementation Method 2
using a smooth, curved surface geometry and tessellated panels to avoid corner formation, allowing for a gradual change in cross-sectional shape
Data Source
Figure 1~2
Figure 3a~3b
Figure 4a~4b
AI summary
The present invention relates to an exhaust nozzle for fluidic-thrust vectoring, comprising an elongate channel for directing exhaust gasses having first and second ends. The elongate channel has an inlet at the first end comprising a continuous curved cross-sectional shape and an exit at the second end having a polygonal cross-sectional shape. In a preferred embodiment, the exhaust nozzle has a rectangular cross-sectional exit. A jet engine and an aircraft having the exhaust nozzle are also provided.