A gas passage for a gas turbine engine, which allows for quicker and easier determination of the condition of a liner within the gas passage without the need for dismantling the entire gas passage, or irreparably damaging large sections of the liner. The gas passage comprises a casing with one or more plugs which are at least partly coated in a material matching the material composition of the lining, which can be removed from the gas passage in order to analyse the condition of the lining material.

Flow control system systems and techniques are described. A flow control system, such as a thruster, includes an annular rotor within an annular housing. The annular rotor rotates about a central axis relative to the annular housing. The flow control system includes rotor blades with respective bases that are coupled to the annular rotor, and with respective tips directed toward the central axis. The flow control system includes a first actuator that rotates the annular rotor about the central axis relative to the annular housing, thus also rotating the rotor blades about the central axis relative to the annular housing. The flow control system includes a second actuator that rotates the rotor blades relative to the annular rotor. Actuation of the second actuator rotates a rotor blade about a rotor blade axis that extends from a base of the rotor blade toward the central axis.

Flow control system systems and techniques are described. A flow control system, such as a thruster, includes an annular rotor within an annular housing. The annular rotor rotates about a central axis relative to the annular housing. The flow control system includes rotor blades with respective bases that are coupled to the annular rotor, and with respective tips directed toward the central axis. The flow control system includes a first actuator that rotates the annular rotor about the central axis relative to the annular housing, thus also rotating the rotor blades about the central axis relative to the annular housing. The flow control system includes a second actuator that rotates the rotor blades relative to the annular rotor. Actuation of the second actuator rotates a rotor blade about a rotor blade axis that extends from a base of the rotor blade toward the central axis.

Disclosed is a system including a turbine having a plurality of blades being spaced circumferentially around a shaft. A plurality of dispensers is included. Each dispenser of the plurality of dispensers is positioned facing the open surface of the plurality of blades and directs discharged fluid toward the open surface of the plurality of blades to drive the turbine. A housing encloses the plurality of blades and a portion of each dispenser. A plurality of exhaust pipes is coupled to the housing and extends away from the shaft directing the discharged fluid out of the housing. Each exhaust pipe corresponds to a respective dispenser of the plurality of dispensers. A controller is in communication with the plurality of dispensers and is configured to control the plurality of dispensers.

Disclosed is a system including a turbine having a plurality of blades being spaced circumferentially around a shaft. A plurality of dispensers is included. Each dispenser of the plurality of dispensers is positioned facing the open surface of the plurality of blades and directs discharged fluid toward the open surface of the plurality of blades to drive the turbine. A housing encloses the plurality of blades and a portion of each dispenser. A plurality of exhaust pipes is coupled to the housing and extends away from the shaft directing the discharged fluid out of the housing. Each exhaust pipe corresponds to a respective dispenser of the plurality of dispensers. A controller is in communication with the plurality of dispensers and is configured to control the plurality of dispensers.

A measurement system for a gas turbine engine is provided. The measurement system comprises a sensor assembly. The measurement system also includes multiple sensors coupled to the sensor assembly. The sensor assembly is configured to be removably inserted within a space defined by a circumferential track embedded within an inner diameter of a casing of the gas turbine engine without having to disassemble the casing.

A measurement system for a gas turbine engine is provided. The measurement system comprises a sensor assembly. The measurement system also includes multiple sensors coupled to the sensor assembly. The sensor assembly is configured to be removably inserted within a space defined by a circumferential track embedded within an inner diameter of a casing of the gas turbine engine without having to disassemble the casing.

A turbocharger assembly including a housing, a shaft, and turbine and compressor wheels mounted on opposite ends of the shaft. The shaft is rotatably supported within the housing by a bearing cartridge that includes turbine-side and compressor side ball-bearing assemblies that are longitudinally spaced by a spacer. There are two times as many rows of ball-bearings included in the turbine-side ball-bearing assembly compared to the compressor-side ball-bearing assembly. The spacer slides over and rotates with the shaft and has at least one flat. An optical sensor extends through the housing and an optical sensor opening in the bearing cartridge to prevent the bearing cartridge from rotating within the housing. The optical sensor detects rotational speed of the spacer by counting the number of times the flat(s) passes by the optical sensor during a pre-determined time interval.

Apparatus and associated methods relate to a system for detecting foreign object debris ingested into an aircraft engine. The system detects such foreign object debris by projecting a beam of light over an inlet of the aircraft engine. When foreign object debris is ingested into the aircraft engine, it intercepts the beam of light and scatters a back-scattered portion of the intercepted beam of light. An optical detector is configured to detect the back-scattered portion of the intercepted beam of light. A processor is configured to determine whether foreign object debris is ingested by the aircraft engine based on a comparison of a threshold value with a signal indicative of the back-scattered portion generated by the optical detector.

A fan assembly includes a fan duct, an inlet fan, an outlet guide vane assembly, and a control system. The inlet fan includes fan blades adapted to rotate about a central axis to force fan exit air toward an aft end of the fan duct. The outlet guide vane assembly is located in the fan duct downstream of the inlet fan and is configured to adjust a direction of the fan exit air. The outlet guide vane assembly includes a plurality of guide vanes that extend radially relative to the central axis and are configured to rotate to a first vane-pitch angle. The control system is configured to rotate the guide vanes redirect the fan exit air, vary a pressure downstream of the fan inlet, minimize intake flow distortion experienced by the inlet fan, reduce inlet fan vibratory response and/or improve fan operability margins.