A method and apparatus for maintaining integrally bladed rotors (IBR) includes using first vibration data from a IBR vibration apparatus of a first IBR to determine a set of values for a corresponding set of inherent vibratory properties based on a reduced order model for an IBR type to which the first IBR belongs. Shape data indicating an initial shape of a surface of a first blade is used, with repair data that indicates a candidate repair to form a restored shape, to determine a change in a value of an inherent blade section vibratory property of the set of inherent vibratory properties. A condition of the first IBR is determined based at least in part on the change in the value of the inherent blade section vibratory property. The first IBR is maintained based on the condition.

A method of calibrating a gas turbine engine having a propulsive fan, and an engine core, the method including: measuring a total thrust generated by the engine; measuring the thrust generated by the engine core; measuring first and second engine performance parameters; based on the total thrust and engine core thrust, determining a thrust generated by the propulsive fan; providing a first power setting parameter associating the fan thrust with the first engine performance parameter; and providing a second power setting parameter associating the engine core thrust with the second engine performance parameter.

A method for testing a turbojet engine for an aircraft in a U-shaped or open-air test bench includes: (a) visual inspection of the test bench and of the turbojet engine; and (b) testing of the turbojet engine in the test bench. During the test, the turbojet engine bears test equipment with sensors, other sensors being housed in the test bench. The test bench includes an augmented-reality system performing the step of (a) visual inspection in the test bench in order to detect a possible major anomaly in the test bench. The step of (a) visual inspection is intended to check the conformity of the test conditions, and especially those of the test equipment or that of the test bench as a whole. The method performs the step of (b) testing only in the absence of an anomaly.

The flow rate control device includes a main plate corresponding to an inner diameter and including a through hole which is formed at the center thereof and through which a fluid flows, a sub-plate corresponding to a size of the through hole, disposed in front of the main plate, and applied with a pressure of the flowing fluid, and an expansion and contraction flow path formed to connect the through hole and a circumference of the sub-plate to each other and expanded and contracted by the pressure applied to the sub-plate. The expansion and contraction flow path includes a plurality of holes which are formed in a side surface thereof and through which the flow flows, and has a cross-sectional area changed by the pressure to control a flow rate.

A method of treating a component adapted for use in a gas turbine engine is described herein. The component may comprise ceramic matrix composite materials. The treatment to the ceramic matrix composite component may reduce or eliminate the wear or damage of crack propagation in the ceramic matrix composite component.

Ice detection test apparatuses, systems, and methods are disclosed. In some cases, ice detection and precautionary system shut-down event reduction systems and related methods are provided. The system utilizes a turbine engine ice detection apparatus that includes and engine pressure simulation device, an air moving device, and a first air pressure sensor associated with the engine pressure simulation device. The embodiment further includes an ice monitor controller that receives inputs from the first air pressure sensor and at least one second sensor located adjacent a turbine engine intake. The ice monitor controller performs comparisons of inputs from these sensors against each other and stored values to determine actual icing conditions then generate warnings on a display to an operator. The exemplary control section has multiple modes including manual, semi-manual and automatic.

Disclosed is a cart (2) for transporting an aircraft engine, comprising a base frame (4) equipped with wheels (6) for riding on a floor; at least two engine arms (14, 16) extending horizontally and movable vertically relative to the base frame, structured and designed for supporting the aircraft engine; and at least two adapter arms (20) extending horizontally at a higher level than the at least two engine arms, structured and designed for supporting an adapter coupled at the top of the aircraft engine. Disclosed is also a method of transporting an aircraft engine to a test cell.

A method can comprise: generating, via a processor, a digital representation of a portion of a repaired bladed rotor, the digital representation based on a geometrical dimensions determined from an inspection of an inspected bladed rotor and a repair blend profile for a defect of the inspected bladed rotor; performing, via the processor, a structural simulation on a structural model, the structural model based on the digital representation of the repaired bladed rotor; performing, via the processor, an aerodynamic simulation on an aerodynamic model, the aerodynamic model based on the digital representation of the repaired bladed rotor; and determining, via the processor, whether results from the structural simulation and the aerodynamic simulation meet an experience based criteria for the repaired bladed rotor.

A method of projecting effects of blade modes onto rotor modes can comprise receiving, via a processor, a modal domain for an ideal bladed rotor and each blade of an inspected bladed rotor; determining, via the processor, whether a mode in the modal domain is at least one of an isolated mode and within a cluster of modes; analyzing, via the processor, the mode individually in response to the mode being isolated; and analyze, via the processor, the cluster of modes together in response to the mode being within the cluster of modes.

A method is disclosed herein. The method can comprise: receiving, via a processor, scanner data from an inspection system for a bladed rotor, the scanner data including a point cloud defining an inspected bladed rotor, the scanner data including a first data size; generating, via the processor, a reduced data set from the scanner data, the reduced data set having a second data size that is less than the first data size; and transmitting, via the processor, the reduced data set to an analysis system for the inspected bladed rotor.