Banca de QUALIFICAÇÃO: RAMON CARNEIRO

Uma banca de QUALIFICAÇÃO de MESTRADO foi cadastrada pelo programa.
STUDENT : RAMON CARNEIRO
DATE: 11/12/2019
TIME: 15:00
LOCAL: Auditório do CTEC - UFRN
TITLE:

ANALYTICAL STUDY OF THE DEMONSTRATOR OF SUPERSONIC COMBUSTION TECHNOLOGY

KEY WORDS:

Supersonic combustion; scramjet; hypersonic airbreathing propulsion.

PAGES: 76
BIG AREA: Engenharias
AREA: Engenharia Mecânica
SUMMARY:

With high potential to be use in space access missions, studies on hypersonic airbreathing vehicle based on supersonic combustion (scramjet) are strategic and attract the attention of que world scientific community. Research about this technology is carried out at the Universidade Federal do Rio Grande do Norte (UFRN) by the Graduate Program in Mechanical Engineering (PPGEM). This work is a theoretical analytical project (engineering approach) of a scramjet technology demonstrator configured to use hydrogen fuel and fly at an altitude of 30 km at a speed of 2051 m / s, corresponding to the number of Mach 6.8. A one-dimensional analytical approach was applied, where calculation routines were applied with the main theoretical equations, according to a set of initial considerations. One-dimensional compressible flow based on oblique shock wave theory, one-dimensional compressible flow with heat addition theory (Rayleigh flow) and one-dimensional expansion wave theory (Prandtl-Meyer) coupled to the area ratio were used as methodologies and theoretical formulation to describe the main fluid and thermodynamic processes of the compression, combustion and expansion section, respectively, of the scramjet engine. This work proposed to design the main components of a scramjet technology demonstrator using a series of criteria and optimizations. Three flat compression ramps, optimized by the method of maximum pressure recovery, were determined the external compression section of the vehicle. The objective was to obtain a compression system capable of compressing the air flow to produce sufficiently high temperature levels to self-ignite the injected fuel (hydrogen) in the combustion chamber. In the expansion section, an expansion angle configuration capable of producing vehicle trailing edge pressures equal to the undisturbed flow (Free stream) of the atmosphere at design altitude of 30 km (1197 Pa) was investigated. As a global assessment of the projected scramjet behavior, the thermodynamic properties and velocity of a current line passing through the leading edge of the vehicle to the trailing edge of the vehicle were evaluated and the non-installed thrust calculated as a performance parameter. In the combustion section, two approaches were evaluated, the first disregarding the fuel injection in the combustion chamber (power-off), representing the free flight conditions without combustion. This configuration was not able to produce positive thrust to the vehicle and a gradual deceleration is expected. Then, the hydrogen injection at the minimum sonic velocity into the power-on chamber was considered, which resulted in the burning of the fuel and the addition of energy to the system. Consequently, analytical results showed that this configuration was able to achieve positive thrust, indicating that the scramjet engine has the ability to generate propulsion to the designed vehicle.

BANKING MEMBERS:
Externo ao Programa - 2524058 - DOUGLAS DO NASCIMENTO SILVA
Externo ao Programa - 1808127 - JOSE HENRIQUE FERNANDEZ
Presidente - 209696 - PAULO GILBERTO DE PAULA TORO