James R. Hulka

TL;DR: A detailed survey of liquid-propellant rocket engine throttling can be found in this paper, where several methods of throttling are discussed, including high pressure drop systems, dual-injector manifolds, gas injection, multiple chambers, pulse modulation, throat throttling, movable injector components, and hydrodynamically dissipative injectors.

TL;DR: In this paper, the authors discuss the various internal programs at the NASA Marshall Space Flight Center using additive manufacturing to develop combustion devices hardware, including thrust chamber injectors, injector components such as faceplates, regeneratively cooled combustion chambers, regenerative-cooled combustion nozzles, gas generator and preburner hardware, and augmented spark igniters.

TL;DR: A detailed survey of liquid-propellant rocket engine throttling can be found in this article, where several methods of LRE throttling are discussed, including high-pressure-drop systems, dual-injector manifolds, gas injection, multiple chambers, pulse modulation, throat throttling, movable injector components, and hydrodynamically dissipative injectors.

TL;DR: In this article, the fluid mechanics of a liquid swirl injector element at various chamber backpressures were investigated and the film thickness and spray angle near the nozzle exit were measured by shadowgraphy.

TL;DR: In this article, single element and three-element injectors were hot-fire tested with liquid oxygen and ambient temperature gaseous hydrogen propellants at The Pennsylvania State University Cryogenic Combustor Laboratory from May to August 2005.