Abstract: A particle separator for a gas turbine engine is disclosed. The particle separator includes flow dividers operable to divide flow in a gas turbine engine particle separator and flow scavengers operable to scavenge flow in a gas turbine engine particle separator.

Abstract: A particle separator for a gas turbine engine is disclosed. The particle separator includes flow dividers operable to divide flow in a gas turbine engine particle separator and flow scavengers operable to scavenge flow in a gas turbine engine particle separator.

Abstract: A particle separator for a gas turbine engine is disclosed. The particle separator includes flow dividers operable to divide flow in a gas turbine engine particle separator and flow scavengers operable to scavenge flow in a gas turbine engine particle separator.

Abstract: A particle separator for a gas turbine engine is disclosed. The particle separator includes flow dividers operable to divide flow in a gas turbine engine particle separator and flow scavengers operable to scavenge flow in a gas turbine engine particle separator.

Abstract: A particle separator for use in connection with a gas turbine engine is disclosed. The particle separator extends circumferentially less than 360 degrees between a first end and a second end. In one embodiment, an inner scavenge conduit is spaced radially inward from an outer scavenge conduit. An inlet can be located between the outer scavenge conduit and the inner scavenge conduit and adapted to receive airflow. A plurality of separated airflow paths can be located between the inner and outer scavenge conduits. The outer scavenge conduit and the inner scavenge conduit can be adapted to receive particles separated from the inlet airflow as the inlet airflow passes along the curved separating portion.

Abstract: A particle separator for separating particles and/or materials entrained in a flow of air is disclosed. The particle separator includes an annular inlet defined by an outer shroud and an inner shroud. An upper forward flow divider and a lower forward flow divider is disposed within the annular inlet. A first and second radially spaced annular flow divider is adapted for directing said flow of air into at least a first, second, third and fourth flow passageway. At least four curved flow splitters are utilized for separating particles and/or materials entrained in the flow of air as it passes through the first, second, third and fourth flow passageways.

Abstract: A pulsed detonation engine wave rotor apparatus and method of using a pressure wave to compress a buffer gas disposed within the engine flow passages. The high pressure buffer gas is routed out of the wave rotor and subsequently reintroduced to the wave rotor to discharge and scavenge the latter stages of the combustion gas remaining under the engine flow passages.

Abstract: A thrust vectoring system comprising a working fluid source mounted to an aircraft, and a vectoring nozzle connected to the working fluid source which has an extendable conduit defining a passage from an inlet to an outlet. The passage is adjustable so that the direction of the working fluid exiting the outlet is different than the working fluid entering the inlet when the conduit of the vectoring nozzle is extended. This conduit provides a way to change the direction of working fluid exiting the nozzle and correspondingly change the thrust vector of the aircraft. A directing member such as a guide vane or door is mounted to the conduit adjacent the outlet to further direct the working fluid exiting the outlet. Directing members provide a way to refine the thrust vector without changing the extension of the segmented conduit. Another aspect of the present invention is to provide an adapter to connect the vectoring nozzle to a working fluid source with an annular outlet.