MUMBAI, India, Sept. 28 -- Intellectual Property India has published a patent application (202641113375 A) filed by J. J. College Of Engineering And Technology on September 22, 2026, for A Compact Axisymmetric Converging–diverging Nozzle With Optimized Throat And Smooth Expansion Profile For Enhanced Propulsive Performance.
Inventors include Mr. T. Kumarasan; Ms. S. Maria Mercy; Mr. P. Jermia Arockia Pravin; Sriladevi. M; Mishal. M; Lakshmi Priyadharshini. M; Rizwanul Janna. U; Sivanathan; Siva Prakash Kannan. P; Harish. R; and Sankar. P.
The application for the patent was published on September 25, 2026, under issue no. 39/2026.
Abstract: The present invention relates to a compact axisymmetric converging–diverging nozzle designed for efficient conversion of high-pressure fluid energy into high-velocity exhaust flow in propulsion and fluid-flow applications. The proposed nozzle comprises an inlet flange, a converging section, a reduced-area throat region, and a diverging expansion section terminating in an enlarged circular outlet. The internal contour of the nozzle is continuously profiled to provide a smooth reduction in flow area toward the throat and controlled expansion downstream of the throat. The geometry is configured to minimize abrupt changes in flow direction and area, thereby reducing flow separation, pressure losses, and undesirable flow disturbances during operation. The optimized throat region facilitates controlled acceleration of the working fluid, while the divergent section promotes efficient expansion and recovery of kinetic energy for improved exhaust velocity and propulsive performance. The compact construction enables the nozzle to be integrated into small-scale aircraft propulsion systems, unmanned aerial vehicles, gas turbines, rocket propulsion systems, experimental propulsion units, and other high-speed fluid-flow devices. The nozzle may be manufactured using metallic, ceramic, composite, or additive-manufacturing techniques and can be dimensionally scaled according to the required mass-flow rate and pressure ratio. The proposed configuration provides a simple, lightweight, manufacturable, and aerodynamically optimized nozzle capable of improving flow efficiency and propulsion performance compared with conventional abruptly contoured nozzle configurations.
Disclaimer: Curated by HT Syndication.
