Preliminary QCSEE program test results

The QCSEE (Quiet, Clean, Short-Haul Experimental Engine) program has entered the engine test phase. Overall design and advanced technology incorporated into the two engines in the program were described. In addition, preliminary engine test results are presented and compared to the technical requirements the engines were designed to meet

A review of the QCSEE program

A description of the overall Quiet Clean Short-haul Experimental Engine Program is presented. The design of the two experimental engines in the program is essentially completed. The engine designs are described and projections of their performance presented. Finally, the advanced technology elements being incorporated into the engines are discussed

Apparatus for igniting solid propellants Patent

Solid propellant ignition with hypergolic fluid injected to predetermined portions of propellan

Method of igniting solid propellants Patent

Method for igniting solid propellant rocket motors by injecting hypergolic fluid

Evaluation of hydrogen fuel in a full-scale afterburner

Combustion efficiency of hydrogen fuel for varying afterburner configuration

Temperature Histories in Ceramic-Insulated Heat-Sink Nozzle

Temperature histories were calculated for a composite nozzle wall by a simplified numerical integration calculation procedure. These calculations indicated that there is a unique ratio of insulation and metal heat-sink thickness that will minimize total wall thickness for a given operating condition and required running time. The optimum insulation and metal thickness will vary throughout the nozzle as a result of the variation in heat-transfer rate. The use of low chamber pressure results in a significant increase in the maximum running time of a given weight nozzle. Experimentally measured wall temperatures were lower than those calculated. This was due in part to the assumption of one-dimensional or slab heat flow in the calculation procedure

Advanced subsonic transport propulsion

A brief review of the current NASA Energy Efficient Engine (E(3)) Project is presented. Included in this review are the factors that influenced the design of these turbofan engines and the advanced technology incorporated in them to reduce fuel consumption and improve environmental characteristics. In addition, factors such as the continuing spiral in fuel cost, that could influence future aircraft propulsion systems beyond those represented by the E(3) engines, are also discussed. Advanced technologies that will address these influencing factors and provide viable future propulsion systems are described. The potential importance of other propulsion system types, such as geared fans and turboshaft engines, is presented