An air intake plenum (22) for a gas turbine engine (20) is provided that includes an axial centerline (30), first and second gas path surfaces (58, 60), and a plurality of struts (42). The gas path surfaces (58, 60) are spaced apart from one another and de...

A system (200) includes one or more debris sensors or particulate sensors (71, 72, 73) are used to sense engine inlet debris (6) or particulate matter which are drawn into the engine (100) during flight, in real-time. The system (200) employs that informat...

An aircraft having an engine and a throttle thereof. The throttle has a throttle body (1), the throttle body (1) is provided with a cavity (10) and comprises an inlet port (11) and an outlet port (12) both of which are connected to the cavity (10); a plura...

Various systems for processing air are disclosed. In one embodiment, an air processing system (4) includes: an inlet manifold (5) adapted to receive compressor discharge air from multiple turbine compressors (2); an air processing system (4) fluidly connec...

Disclosed herein are methods and systems for gas turbine inlet air flow rate measurement using inert gas. In an embodiment, a gas meter (125) may measure the concentration of an injected gas into an air flow. A processor (135) may receive the measurement o...

An inlet apparatus for a gas turbine engine includes: a fan duct adapted to surround at least one row of rotating fan blades, the fan duct having a circular frontal area, and defining a first inlet plane; and an outer duct surrounding the fan duct, the out...

The present application provides an inlet air fogging system (100) for a gas turbine engine (110). The inlet air fogging system (100) may include a fogging nozzle array (270) and a fogging control system (320) in communication with the fogging nozzle array...

An inlet (18) of a nacelle (16) for channeling inlet airflow to a fan (28) of a gas turbine engine (12) includes a forward lip (40) and an inner surface (46). The forward lip extends around a centerline axis (20) of the engine and is adapted to accommodate...

The missile has a ramjet with a combustion chamber (1) whose inner side is lined with a thermal insulation layer. Cylindrical combustion chamber housing has air inlet openings (4, 5) that are arranged in rows. Fuel rich hot gas formed from a high-energy so...

The incoming edge (7) of an outer casing (6) is connected to a ring-shaped plate (9) aligned perpendicular to the axis (10) of an axial flow part (2). The plate is mirror symmetric in a direction perpendicular to the axis of the axial flow part, and unsymm...