MUMBAI, India, Feb. 27 -- Intellectual Property India has published a patent application (202641018013 A) filed by Malla Reddy Deemed To Be University; Ms S. C Sireesha; Dr A. Raveendra; and Dr K. Bharadwaja, Hyderabad, Telangana, on Feb. 18, for 'pressure recovering inlet for jet propulsion systems.'
Inventor(s) include Malla Reddy Deemed To Be University; Ms S. C Sireesha; Dr A. Raveendra; Dr K. Bharadwaja; Dr. Jaganathan Muthusamy; Dr. T V Sarath Kumar; Ms. Chetti Venkateswarlu; Dr Kandhagatla Ramakrishna; Dr D. S. Chandra Mouli; and Dr S. Uday Bhaskar.
The application for the patent was published on Feb. 27, under issue no. 09/2026.
According to the abstract released by the Intellectual Property India: "An inlet system for a supersonic combustion ramjet (scramjet) engine is disclosed, configured to facilitate engine ignition and operation across an expanded Mach range from Mach 3.0 to Mach 9.0. The system comprises an optimized inlet geometry designed to maintain efficient compression of free-stream supersonic air, increasing temperature and pressure through a series of internal or external compression ramps. By precisely managing flow deceleration, the apparatus ensures the pressure and density of the flow entering the burner are significantly higher than the free-stream conditions, enabling stable combustion without the need for an intermediate ramjet propulsion stage. The geometry is further refined to mitigate efficiency losses typically encountered at flight speeds exceeding Mach 6.0. Computational fluid dynamics (CFD) analysis, conducted via FLUENT, characterizes the flow field to ensure the transition from supersonic intake to hypersonic combustion is optimized for reduced vehicle weight and mechanical complexity. The design enables a direct transition from turbojet-assisted speeds (approximately Mach 3.0 to 4.0) to full scramjet operation."
Disclaimer: Curated by HT Syndication.
