17948870. EXHAUST NOZZLE ASSEMBLY FOR AN AIRCRAFT PROPULSION SYSTEM simplified abstract (PRATT & WHITNEY CANADA CORP.)
Contents
- 1 EXHAUST NOZZLE ASSEMBLY FOR AN AIRCRAFT PROPULSION SYSTEM
- 1.1 Organization Name
- 1.2 Inventor(s)
- 1.3 EXHAUST NOZZLE ASSEMBLY FOR AN AIRCRAFT PROPULSION SYSTEM - A simplified explanation of the abstract
- 1.4 Simplified Explanation
- 1.5 Potential Applications
- 1.6 Problems Solved
- 1.7 Benefits
- 1.8 Potential Commercial Applications
- 1.9 Possible Prior Art
- 1.10 Original Abstract Submitted
EXHAUST NOZZLE ASSEMBLY FOR AN AIRCRAFT PROPULSION SYSTEM
Organization Name
Inventor(s)
Michel Labrecque of Sainte-Julie (CA)
EXHAUST NOZZLE ASSEMBLY FOR AN AIRCRAFT PROPULSION SYSTEM - A simplified explanation of the abstract
This abstract first appeared for US patent application 17948870 titled 'EXHAUST NOZZLE ASSEMBLY FOR AN AIRCRAFT PROPULSION SYSTEM
Simplified Explanation
The exhaust nozzle assembly for a propulsion system includes a primary nozzle, an outer shroud, an ejector nozzle, and an actuator. The primary nozzle extends along an exhaust centerline and has a downstream axial end. The outer shroud surrounds the primary nozzle. The ejector nozzle extends axially between a first axial end and a second axial end, with the second axial end forming a nozzle exit plane. The ejector nozzle converges from the first axial end to the second axial end and forms a mixing cross-sectional area with the primary nozzle at the downstream axial end. The actuator is mounted on the ejector nozzle and can move it between a first and second position to control the mixing cross-sectional area.
- The exhaust nozzle assembly includes a primary nozzle, outer shroud, ejector nozzle, and actuator.
- The ejector nozzle converges from the first axial end to the second axial end and forms a mixing cross-sectional area with the primary nozzle.
- The actuator can move the ejector nozzle to control the mixing cross-sectional area.
Potential Applications
The technology can be applied in aircraft propulsion systems, rocket engines, and other aerospace applications where precise control of exhaust flow is required.
Problems Solved
1. Improved control of exhaust flow for enhanced propulsion efficiency. 2. Enhanced performance and maneuverability of propulsion systems.
Benefits
1. Increased fuel efficiency and overall performance. 2. Greater control and flexibility in propulsion system operation. 3. Potential for reduced emissions and environmental impact.
Potential Commercial Applications
Optimized exhaust nozzle assemblies can be utilized in commercial aircraft, military jets, space exploration vehicles, and other aerospace platforms to improve efficiency and performance.
Possible Prior Art
Prior art may include patents related to exhaust nozzle designs, propulsion system components, and aerospace engineering innovations. Research into existing patents in these areas can provide insights into similar technologies and advancements in the field.
Unanswered Questions
How does the actuator precisely control the movement of the ejector nozzle?
The specific mechanism by which the actuator adjusts the position of the ejector nozzle to control the mixing cross-sectional area is not detailed in the abstract. Further information on the actuator design and operation would be needed to fully understand this aspect of the technology.
What materials are used in the construction of the exhaust nozzle assembly?
The abstract does not mention the materials used in the construction of the primary nozzle, outer shroud, ejector nozzle, and actuator. Understanding the materials selection can provide insights into the durability, performance, and cost-effectiveness of the technology.
Original Abstract Submitted
An exhaust nozzle assembly for a propulsion system include a primary nozzle, an outer shroud, an ejector nozzle, and an actuator. The primary nozzle extends along an exhaust centerline. The primary nozzle includes a downstream axial end. The outer shroud surrounds the primary nozzle. The ejector nozzle extends axially between a first axial end and a second axial end. The second axial end forms a nozzle exit plane for the exhaust nozzle assembly. The ejector nozzle converges in a direction from the first axial end to the second axial end. The ejector nozzle forms a mixing cross-sectional area between the primary nozzle and the ejector nozzle at the downstream axial end. The actuator is mounted on the ejector nozzle. The actuator is configured to move the ejector nozzle between a first position and a second position, relative to the outer shroud, to control an area of the mixing cross-sectional area.
