An inspection system for fan rotor blades in a gas turbine engine is provided. The gas turbine engine has a sensor that provides a fan rotor stage speed signal. The system includes a plurality of cameras and light sources and a system controller. The cameras are controllable to image a leading edge of a fan rotor blade. Each respective camera and light source is mounted with a static structure disposed forward of the fan rotor blade stage. The system controller is in communication with stored instructions that when executed cause the system controller to monitor the speed of the fan rotor stage during an engine shutdown; upon the fan rotor stage speed reaching a first value, control the light sources to selectively illuminate the fan rotor blades, and control the cameras to image the fan rotor blades, and provide inspection information using signals representative of the captured images.

A method of stopping an engine of a rotorcraft in overspeed, the engine comprising a gas generator and a power assembly. When the engine is in operation, the engine is automatically stopped when the following three conditions are satisfied simultaneously: a torque (Tq) measured on the power assembly is below a predetermined torque threshold (Tq1); and a speed of rotation referred to as a first speed of rotation (N1) of the gas generator is above a threshold referred to as a first speed threshold (S1); and a speed of rotation referred to as a second speed of rotation (N2) of the power assembly is above a threshold referred to as a second speed threshold (S2).

A method of stopping an engine of a rotorcraft in overspeed, the engine comprising a gas generator and a power assembly. When the engine is in operation, the engine is automatically stopped when the following three conditions are satisfied simultaneously: a torque (Tq) measured on the power assembly is below a predetermined torque threshold (Tq1); and a speed of rotation referred to as a first speed of rotation (N1) of the gas generator is above a threshold referred to as a first speed threshold (S1); and a speed of rotation referred to as a second speed of rotation (N2) of the power assembly is above a threshold referred to as a second speed threshold (S2).

A valve control system for a steam turbine that decrease in effective power as well as secure control stability in the event of an electric power system accident is provided. A valve control system for a steam turbine includes an accident detection unit 44 which detects an occurrence of an electric power system accident, a first selection unit 45 which selects, from a plurality of control valves 13 (13a13d) which adjust a volume of steam flowing into a steam turbine, control valves 13 to be rapidly closed according to a scale of the accident detected, and a normal control circuit 11 which continues normal pressure or speed control by the control valves 13 which are not selected.

A valve control system for a steam turbine that decrease in effective power as well as secure control stability in the event of an electric power system accident is provided. A valve control system for a steam turbine includes an accident detection unit 44 which detects an occurrence of an electric power system accident, a first selection unit 45 which selects, from a plurality of control valves 13 (13a13d) which adjust a volume of steam flowing into a steam turbine, control valves 13 to be rapidly closed according to a scale of the accident detected, and a normal control circuit 11 which continues normal pressure or speed control by the control valves 13 which are not selected.

An aircraft comprising a fuselage and propelled by a turbine engine having two coaxial and contrarotating fans, the turbine engine comprising a power turbine having two contrarotating rotors, one of which drives a fan upstream from the turbine, the other a fan downstream from the turbine, each fan comprising a ring of blades, and the assembly of the fans and the power turbine being incorporated at the rear of the fuselage, in the extension of same. The aircraft comprises, for at least one of the fans, a device for blocking the rotation of the fan and a device configured to modify the pitch of the blades of the fan in such a way as to make it operate as a flow straightener with respect to the other fan.

A portable jig and fixture having at least one base plate, a column assembly removably coupled to the at least one base plate, a slide assembly removably coupled to the column assembly, a power feed head removably coupled to the slide assembly, and a spindle unit removably coupled with the slide assembly having a motor removably engaged it. At least one cutter assembly is removably engaged with the spindle unit and at least one drill jig is also removably engaged with the spindle unit. Also, a turbomachine having complementary structure on the compressor discharge casing can engage with the at least one base plate alignment mounting structure on the portable jig and fixture.

An assembly for an aircraft propulsion system includes a propulsor section and an imaging device. The propulsor section includes a propulsor and a structural body. The propulsor includes a plurality of propulsor blades. The structural body forms an outer air flow surface forming a portion of an air flow path through the propulsor section. The imaging device includes a housing and a camera. The housing includes a housing body and a cover. The housing body is mounted in the structural body. The housing body forms a cavity and an opening of the cavity. The cover is pivotable between a stowed position and a deployed position. The camera is disposed in the cavity with the cover positioned in the stowed position. The camera is configured to capture image data of each propulsor blade of the plurality of propulsor blades with the cover positioned in the deployed position.

An assembly for an aircraft propulsion system includes a propulsor section, an imaging device, a plurality of light sources, and a controller. The propulsor section includes a propulsor. The propulsor includes a plurality of propulsor blades. The imaging device is disposed in the propulsor section. The imaging device includes a camera. The plurality of light sources are disposed in the propulsor section. The controller includes a processor in communication with a non-transitory memory storing instructions, which instructions when executed by the processor, cause the processor to: control the plurality of light sources to direct light to the plurality of propulsor blades, control the camera to capture image data of each propulsor blade of the plurality of propulsor blades, and identify a presence or an absence of damage for each propulsor blade of the plurality of propulsor blades using the image data.

A method for barring a rotor of a thermally loaded turbomachine includes stopping normal operation of the turbomachine; providing a barring device for rotating the rotor about a machine axis; coupling the barring device to the rotor; letting the rotor cool down during cool down of the rotor rotating the rotor by means of the barring device. A damage of the machine due to thermally induced buckling during the barring process is avoided by consecutively determining the force or torque applied to the rotor by the barring device for rotating the rotor and/or the circumferential speed of the rotor during barring. The rotation of the rotor is controlled by means of the barring device in dependence of the determined force or torque and/or circumferential speed in order to reduce a bending or imbalance of the rotor, which is due to a nonuniform temperature distribution on the rotor during cool down.