on the occasion of her 10th founding anniversary.

A series of ruthenium alkylidene complexes were adopted to catalyze aqueous-phase reforming of ethanol for H 2 production at readily achievable temperatures (<100 °C). The best results were obtained using (SIMes)Ru(PCy 3 )(3-methyl-2butenylidene)Cl 2 (SIMes, 1,3-bis(2,4,6-trimethylphenyl)-4,5-dihydroimidazol-2-ylidene; PCy 3 , tricyclohexylphosphine) with a fiveday reaction producing a maximum turnover number (TON) of 47,295; this value is the second-largest one known for homogeneously catalyzed ethanol dehydrogenation. Kinetic experiments confirmed that the reforming process undergoes a secondorder reaction kinetics, with both ethanol and water contributing to H 2 production. Analyses of the reaction mixture using an in situ 1 H NMR experiment revealed a possible intermediate coordinated with a hydride ligand, based on which and previous work a plausible mechanism was proposed.

The nozzle is a kind of equipment with a wide range of usage in the aerospace industry, of which its performance is vital for rocket engines by changing the geometry of the inner wall of the pipe section to accelerate the airflow. There are two types of nozzles commonly used: one is a tapered nozzle, and the other is a Laval nozzle. To analyze the flow phenomenon in nozzle is vital before transferring prototype design into industrial production, whether by laboratory experiment or computational simulation. In this paper, two different numerical methods are adopted to simulate gas behavior inside a simplified nozzle with upper and bottom symmetrical bumps. The first is to solve one dimensional Euler equations, and the other is to solve a scalar variable named velocity potential with small disturbance equations (SDE). The solutions under various inlet Mach numbers are compared by analysing the velocity fields and Mach number contours obtained by these two approaches. Similarities and differences between the Euler method and the potential SDE method for subsonic flow and supersonic flow are the key emphases in this work. For either subsonic or supersonic flow, the Mach number distribution along the nozzle’s center line shows a consistent trend for both methods. In contrast, the values of maximum or minimum Mach number have corresponding differences. Moreover, by using potential SDE simulation, several types of shock waves are successfully captured. All results show that the incoming airflow decelerates at the leading edge of the nozzle then accelerates when passing through the bumps, and finally decelerates back to the speed of inlet flow. The difference is that flows with varied Mach numbers has distinct velocity distributions in the nozzle.