Banca de DEFESA: TIAGO ALEIXO DE ARAÚJO

Uma banca de DEFESA de MESTRADO foi cadastrada pelo programa.
STUDENT : TIAGO ALEIXO DE ARAÚJO
DATE: 15/07/2024
TIME: 08:00
LOCAL: Virtual
TITLE:

Conceptual study of a symmetrical internal scramjet demonstrator with three ramps.

KEY WORDS:

supersonic combustion; scramjet; hypersonic airbreathing propulsion, symmetrical internal compression system

PAGES: 107
BIG AREA: Engenharias
AREA: Engenharia Aeroespacial
SUBÁREA: Aerodinâmica
SPECIALTY: Aerodinâmica de Aeronaves Espaciais
SUMMARY:

In this work, a conceptual study of an airbreathing propulsion system based on supersonic combustion (scramjet technology) of an aerospace vehicle flying at hypersonic speed of 2050 m/s at an altitude of 30 km was developed. The objective was to study a symmetrical internal configuration with three ramps in the compression section and compare it with the mixed external and internal configuration with three ramps and same turning angles. An analytical theoretical methodology (engineering approach) was applied using the oblique shock wave theory in the compression section, the Rayleigh theory of heat addition in one-dimensional flow, with constant area cross section, no considering fuel mass, in the combustion chamber, and the area ratio theory coupled with the Prandtl-Meyer expansion theory in the expansion section. The flow properties without fuel injection at the combustion chamber (power-off) and with hydrogen fuel injection, burning atmospheric air-hydrogen fuel, in the flow at supersonic speed (power-on), were analyzed. The atmospheric air captured by the inlet of the scramjet vehicle is compressed and decelerated to a condition of supersonic speed and a temperature higher than the spontaneous ignition temperature of the fuel. Considering power-off condition, the flow at the expansion section obtained a velocity lower than the flight speed, due to the increase in entropy. However, in the power-on condition, the combustion products of the atmospheric air-hydrogen fuel mixture provide an increase in the scramjet's flight speed, producing uninstalled thrust of 402.64N and specific impulse of 4164.02s. Finally, a performance analysis of the scramjet developed was carried out considering parameters such as propulsive efficiency, thermal efficiency and global efficiency.

COMMITTEE MEMBERS:
Presidente - ***.408.158-** - PAULO GILBERTO DE PAULA TORO - ITA
Interno - 1451488 - JOÃO CARLOS ARANTES COSTA JÚNIOR
Interno - 1647050 - SANDI ITAMAR SCHAFER DE SOUZA
Externa à Instituição - HEIDI KORZENOWSKI - UNIVAP