Numerical procedures to describe the dispersion, evaporation and combustion of a polydisperse liquid fuel in a turbulent oxidizer are presented. Direct Numerical Simulation (DNS) allows one to describe accurately the evolution of the fully compressible gas-phase coupled with a Lagrangian description in order to describe two-phase flows. Standard coupling is used for the Eulerian/Lagrangian syst...

Hybrid rocket engine (HRE) performance is dependent on fuel/oxidizer selection and fuel grain geometry. A literature review was performed to identify key trends findings related the application of additive manufacturing (AM) systems for HREs. The effects complex combustion port geometries, embedded structures, end-burning systems, along with use metallic additives, turbulators, diaphragms, gel-...

Feedforward neural networks were used to model three parameters during the Space Shuttle Main Engine startup transient. The three parameters were the main combustion chamber pressure, a controlled parameter; the high pressure oxidizer turbine discharge temperature, a redlined parameter; and the high pressure fuel pump discharge pressure, a failure-indicating performance parameter. Network input...

This paper investigates the effect of ethanol-unleaded gasoline blends (E0,E10,E25,E35,andE65) computer interfaced, four-stroke single cylinder compression ignition engine. The said engine wasconverted to spark ignition and carburetion to suit ethanol fuel. A suitable provision was provided on theengine to vary the compression ratio thereby making the engine adaptable to operate at lowercompres...

Formulations of aluminum nano particles for energy applications have been intensely investigated over the past few decades for their attractive energy release rate. They significantly affect propellant burn rates, enhance detonation properties, and are also used in thermite formulations (“Super-Thermites”) [1]; however, the reactive properties remain poorly understood. The mechanism behind thes...

In the period from 2019 to 2022, joint American–Russian space experiment (SE) Flame Design (Adamant) was carried out on International Space Station (ISS). The purpose of SE study mechanisms control soot formation in a spherical diffusion flame (SDF) formed around porous sphere (PS), and radiative extinction SDF under microgravity conditions. objects this were “normal” “inverse” SDFs gaseous eth...

To meet increasingly stringent emission regulations modern internal combustion engines require highly accurate control of the air-to-fuel ratio. The performance of the conventional air-to-fuel ratio feedback loop is limited by the combustion delay between fuel injection and engine exhaust, and by the transport delay for the exhaust gas to propagate to the air-to-fuel ratio sensor location. The ...

A Nd:YAG-pumped dye-laser system was used to two-photon excite oxygen atoms at 225.6 nm in an atmosphericpressure CH(4)-N(2)O-N(2) flame. Subsequent emission at 844.7 nm from the directly populated state as well as a stronger emission at 777.5 nm that was due to the O(3p(3)P ? 3p(5)P) collisional-energy transfer process was monitored. Two-photon-resonant oxygen-atom and hydrogen-atom (656.3-nm)...

A spectrometer system was constructed for measurement of transient species in flames by absorption of ultraviolet radiation. The output of a xenon arc lamp was used as the source of radiation, which was focused through the flame and onto a monochromator equipped with an intensified silicon diode array detector. The system was used to measure absorption by hydroxyl (OH) radical around 306 nm in ...