Eden Schiavinato de SOUZA, Lucas RIBEIRO, Leda VIALTA, Pedro MATOS, Luiz BARRETA, Giannino CAMILLO, Israel RÊGO, Lucas GALEMBECK, Dermeval CARINHANA JR, Pedro LACAVA
DOI Number: XXX-YYY-ZZZ
Conference number: HiSST2024-00222
The relation between the spatial pressure profile and global equivalence ratio was investigated in a hydrogen-fueled supersonic combustor directly connected to a shock tunnel facility. The combustor model comprises an initial constant area section (isolator), followed by a single-hole fuel injection point, a flame-holder cavity, and finally, an expansion ramp. The results were obtained for a freestream inlet flow at Mach 2.7, static temperature of 705 K, and static pressure of 164 kPa, with stagnation conditions at 1,470 K and 3.8 MPa. The global equivalence ratio (ER) ranged from 0.10 to 0.50. Dynamic pressure transducers were installed along the combustor model, schlieren images were used to assess the flow profile, and a high-speed OH* chemiluminescence emission technique was employed to verify the occurrence of supersonic hydrogen combustion. Substantial increases in combustion pressures relative to the reference were observed. These increases were in accordance with theoretical predictions for ER ranging from 0.10 to 0.25, showing an increase of 1.5 to 2.3 times the reference pressure. For ER values between 0.25 and 0.50, the pressure increases stabilized at approximately 2.3 times the reference pressure.