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 define at least a portion of a plenum…
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 information, in conjunction with other engine…
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 plurality of fuel injectors (2), each of the…
A pressure and temperature probe of a gas turbine engine (20) includes a base portion (38) and an airfoil portion (40) extending from the base portion to an end portion located at a distal end of the probe. The airfoil portion includes a leading edge located at an upstream end of the probe relative…
An air intake for a stationary gas turbine engine includes a vertical duct (15) having a front wall (16), a rear wall (17), side walls (18) and a feed opening (50) in the rear wall (17). The front wall (16) and the rear wall (17) are flat and parallel to each other. The side walls (18; 118; 218)…
An air intake system for an aircraft engine includes an air duct having an inlet port to provide fluid communication between the inlet port and the engine and a removable air filter assembly configured to interface with the inlet port of the air duct and a skin of the aircraft. The air filter…
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 connected with the inlet manifold (5), the air…
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 of the gas concentration and calculate an…
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 outer duct including: a first frontal area…
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 (270). The fogging control system (320)…
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 a flow angle (²) of incoming airflow. The…
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 solid propellant in another chamber (49) and…
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 unsymmetric in a direction along the axis of the…