Abstract: The invention is a propulsion system for a V/STOL type aircraft. In detail, the invention comprises a turbofan engine including a fan section, compressor section, combustion section, turbine section and nozzle section. The turbine section comprises a low-pressure turbine portion coupled to and driving the fan section and a high-pressure turbine portion coupled to and driving the compressor section. A lift fan is coupled to the fan section by means of a drive shaft. A clutch is incorporated for decoupling the lift fan from the fan section. A mechanism is incorporated for extracting additional power from the low-pressure turbine portion of the turbine section to drive the lift fan that augments the basic engine thrust for V/STOL operation.

Abstract: A nozzle system for providing improved thrust augmentation for an aircraft lift and/or propulsion system is provided. The unique nozzle structure is designed such that counter-rotating vortices emanate from the nozzle tips. When this unique nozzle configuration is combined with simple slot nozzles in a specific manner a vortex rich flow will result. When a diffuser is placed around this unique combination such that jet pumping is obtained, significant improvement in thrust augmentation is realized from the vortex rich flow mixing with the coflowing secondary air stream.

Abstract: A spray dryer apparatus for contacting a hot gas stream containing gaseous impurities with an aqueous medium containing an absorbent for the impurities to produce a gas stream of reduced impurity content and dried powder products. The apparatus includes a chamber formed symmetrically about a vertical axis and an atomizer means located in an upper portion of the chamber for introducing a finely dispersed spray of the aqueous medium, a conduit for delivering the hot gas stream to the chamber and a gas injection means for receiving a major portion of the hot gas stream from the conduit and introducing it circumferentially about the atomizer means. The gas injection means imparts both axial and angular velocity components to the major portion of the hot gas stream whereby the hot gas stream swirls downwardly through the chamber.The apparatus provides a bypass means for withdrawing a minor portion (about 5 to 25 vol.