The effect of injector design on thrust- chamber erosion.
Control of injector spray and heat transfer properties can reduce erosion of ablative and pyrolytic graphite thrust-chamber throats
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Control of injector spray and heat transfer properties can reduce erosion of ablative and pyrolytic graphite thrust-chamber throats
Relation between injector design and erosion of ablative and pyrolytic graphite thrust chamber throat
Injector spray characteristics in simulated rocket combustion chamber including longitudinal mode pressure oscillations
Analysis, design, and demonstration of high performance injectors for liquid fluorine- gaseous hydrogen propellant combination
Effects of injector face baffle configurations on screech in hydrogen-oxygen rocket engine
Subscale and full scale test firings of M-1 injector to improve combustion efficiency
Formation and properties of liquid sheets suitable for use in rocket engine injectors
Subscale tests of M-1 rocket engine injector performance and chugging stability characteristics
M-1 injector baffles, ablative chamber and start system design and development, using subscale testing
Parker Hannifin Corporation developed the 3-Zone fuel nozzle for NASA's Environmentally Responsible Aviation Program to meet NASAs target of 75 LTO NOx reduction from CAEP6 regulation. The nozzle concept was envisioned as a drop-in replacement for currently used fuel nozzle stem, and is built up from laminates to provide energetic mixing suitable for lean direct injection mode at high combustor pressure. A high frequency fuel valve was also developed to provide fuel modulation for the pilot injector. Final testing result shows the LTO NOx level falling just shy of NASAs goal at 31.
Effect of fuel injector and liner design on performance of turbojet combustor with vapor fuel
Injector imparts a high charge-to-mass ratio to microparticles and injects them into an electrostatic accelerator so that the particles are accelerated to meteoric speeds. It employs relatively large masses in the anode and cathode structures with a relatively wide separation, thus permitting a large increase in the allowable injection voltages.
Operation of high impact rate particle injector for electrostatic accelerator to simulate long-term micrometeoroid bombardment
Effect of pressurant gas injectors during pressurized discharge of liquid hydrogen
Performance tests of shower-head, triplet, and like-on-like liquid hydrazine-fluorine injectors in uncooled rocket engine
Performance tests of low pressure drop coaxial and shower-head injectors for gaseous hydrogen- liquid fluorine rocket chamber
Formation and properties of liquid propellant sheets from fuel injectors on curved deflector surfaces
Working equations for dimensions and orientation of impinging propellant sheets in liquid rocket engine injectors