HYBRID POWER SOURCE SYSTEM FOR ELEVATORS

PATENT GRANTED NO: 202241022817 A

Inventors:
DR. PRAWIN ANGEL MICHAEL, ASSOSIATE PROFESSOR, AEROSPACE ENGINEERING
DR. S. J. VIJAY, PROFESSOR, MECHANICAL ENGINEERING
DR. H. VICTOR DU JOHN, ASSISTANT PROFESSOR,ECE

• Energy management for elevators, particularly to hybrid power source system .

• Relates to energy efficient hybrid power source system with sustainable resources combining solar power, thermo electric module and in-series with DC generator providing an improved power control and energy management.

• The hybrid power source system is configured to retrofit or replace conventional power system making the elevators energy efficient.

• It captures the excess heat generated by the elevator drives during operation and converts it into a reusable energy and reduces the energy consumed by building transportation systems up to 70%, thereby enhancing the power saving capability by 13.2 %.

A HALF COIL MANUFACTURED FROM NOVEL COMPOSITION FOR BRUSHLESS DC MOTOR WINDINGS WITH IMPROVED EFFICIENCY

PATENT GRANTED NO: 202141016081 A

Inventors:
DR. PRAWIN ANGEL MICHAEL, ASSOSIATE PROFESSOR, AEROSPACE ENGINEERING
DR. S. J. VIJAY, PROFESSOR, MECHANICAL ENGINEERING

The invention relates to the composition and manufacture of coil winding for electrical appliances, more particularly a nano-materials based coil winding with improved efficiency as an alternate for conventional copper coil winding.

Supersonic nozzle extension for optimum operation with thrust augmentation

PATENT NO: 202341087944

Inventors:
DR. ALDIN JUSTIN, ASSISTANT PROFESSOR, AEROSPACE ENGINEERING
MR. VATTI SUDEEP REDDY, URK20AE1036, B-TECH AEROSPACE ENGINEERING

This invention describes a novel supersonic nozzle extension designed to optimize engine performance across a broad range of altitudes. The extension mechanism allows for dynamic adjustment of the nozzle's length and diameter, a critical feature for achieving maximum thrust efficiency during flight.

Conventional supersonic nozzles are designed for peak performance at a specific altitude. Operating at significantly lower or higher altitudes can lead to inefficiencies, such as thrust: An improperly sized nozzle can hinder the complete expansion of exhaust gases, resulting in wasted energy and lower thrust output. Backflow: In certain scenarios, an oversized nozzle can cause exhaust gases to flow back into the engine, potentially damaging components and compromising performance.

This innovative supersonic nozzle extension addresses the above said challenges.

Deflagration To Detonation Supersonic Igniter

Patent No: 201941026005

Inventors:
Dr. Aldin Justin Sundararaj, Assistant Professor, Aerospace Engineering
Ms. Vinitha M Samuel PR16AE002, M.Tech batch 2016-18

In deflagration to detonation supersonic igniter the fuel and oxidizer is ignited with a conventional spark plug. The flame thus developed is made to travel through a Shchelkin spiral placed inside the tube. The spiral acted as a blockage and the subsonic flame gets converted to detonation wave. A introduction of secondary source of fuel in the detonating tube results in an effective enhancement of ignition in detonation engines. The supersonic igniter can be used to initiate supersonic /detonating wave in high enthalpy engines like Pulse Detonation Engines (PDE), Continuous Rotating Detonation Engines (CRDE).

Improved Blowing Suction System (IBSS) for enhanced aerodynamic performance in aircraft wing

Patent No: 202041046416 A

Inventors:
Dr. G. Jims John Wewssley, Assistant Professor, Aerospace Engineering
Mr. K. Balaji RPK17AE001, Ph.D scholar

The present invention discloses an Improved Blowing Suction System for enhanced aerodynamic performance of aircraft wing. The Improved Blowing Suction System comprises of disposing on aircraft wing, a Pump connected with an injection port on one end and a suction port on another end to create additional flow over aircraft wing without disturbing main flow and effectively controlling boundary layer separation. The system of the present invention characterized in positioning of the injection port at maximum thickness point (separation point) which is starting point of boundary layer separation in aerofoil and characterized in positioning of suction port at point where circulation is created near trailing edge of aerofoil thereby introducing additional flow at exact location of flow separation and creating suction at location where circulation exists at aerofoil with improved stalling angle of attack and increased lift.