A device enables borescope inspection of turbine blades of a high-pressure turbine stage of a jet engine. The device has a bend-free guide pipe for introducing a flexible borescope. The device also has: a guide for the guide pipe, the guide being configured to provide clear and reproducible positioning and orientation of the guide pipe; and a securing device configured to releasably secure the guide to an outer side of the jet engine. The securing device is configured to adjust the guide to a predetermined orientation with respect to the outer side of the jet engine. The guide pipe is rigid and shaped in such a manner that an end of the guide pipe that is introduced into the jet engine when the guide is orientated correctly is orientable so as to be directed between two predetermined guide blades.

A device for detecting particles in a lubricating oil of a machine, comprising a particle separator; at least one particle detector; a bypass conduit for the particle-concentrating oil, fluidly connected to an oil outlet of the particle separator, concentrating the particles; and wherein the at least one particle detector is operatively mounted on the bypass conduit so as to be able to detect particles in the bypass conduit.

A damage detection system includes one or more emitters, one or more receivers, and a controller. Emitters are arranged to transmit continuous beam or intermittent light pulses toward rotor blades during operation of a turbomachine. Light returns collected at the receivers define a light return amplitude profile. The controller analyzes the light return amplitude profile to identify light amplitude changes indicative of one or more damaged blades. When the light return profile satisfies one or more damage criteria, the controller outputs an indication of blade damage to another turbomachine controller, system, or display.

Systems, methods, and computer readable medium are provided for determining interferometric data and spectral data associated with combustion conditions of a flame in a combustion chamber using a sensor head including a first vacuum cavity, a diaphragm operatively interfaced to an inner portion of the combustion chamber, and an optical sensor interrogator configured on a computing device and coupled to the sensor head via optical fibers. The optical sensor interrogator including an interferometer configured to determine interferometric data associated with the flame based on light transmitted and reflected via a first optical fiber and a spectrometer configured to determine spectral data associated with the flame based on light transmitted via a second optical fiber.

A gas turbine engine for an aircraft. The gas turbine comprises a staged combustion system having pilot injectors and main injectors, a fuel metering system configured to control fuel flow to the pilot injectors and the main injectors, and a fuel system controller. The controller is configured to identify an atmospheric condition, determine a ratio of pilot fuel flow rate for the pilot injectors to main fuel flow rate for the main injectors in response to the atmospheric condition, and inject fuel by the pilot injectors and the main injectors in accordance with said ratio to control an index of soot emissions caused by combustion of fuel therein.

A maintenance system for a flame detector in an enclosure for an industrial machine, such as turbomachine, is disclosed. The maintenance system may include a conduit having an inlet at an exterior of the enclosure and an outlet at an interior of the enclosure. The outlet is adjacent the flame detector. The maintenance system also includes a source of air and a valve fluidly coupling the inlet of the conduit and the source of air. The valve is configured to deliver a compressed air from the source of air through the outlet of the conduit onto a surface of the flame detector, thereby removing contaminants from the surface and/or cooling the surface. A controller can be provided to automatically operate the cleaning and cooling system when a fault signal is observed.

The present invention discloses a method of measuring longitude deformation of blades. The radiation and rotation speed of the blade are collected by an optical probe and a synchronized rotation sensor. The stretch of the blade is able to be determined by the obvious change in the light intensity detected by the optical probe. The precision servo motor keeps driving the optical probe to move upward. The collected radiation is compared with the radiation collected on the previous point. The stretch of the blade is calculated based on position of the blade tip which is determined by the time when the high level radiation from the blade is disappeared. The longitude deformation of the blade is calculated by plugging the stretch into the deformation equation. Mapping the calculated deformation with the number of the blade calculated with rotation speed synchronizing signals to achieve the deformation of all the blades.

The present invention relates to a method for characterizing a coating, in which method a mass and/or a volume of a basic body is/are measured prior to coating; a mass and a volume of the basic body with the applied coating are measured; for characterizing the coating, a density of the coating is determined from the volume and mass measurements; wherein the volume is optically measured.

A component treatment processes and treated gas turbine components are disclosed. The gas turbine treatment process includes laser-removing coating from a substrate of a turbine component to form laser-induced plasma, spectroscopically analyzing the laser-induced plasma, and discontinuing the laser-removing in response to the spectroscopic analyzing. The treated gas turbine component includes a laser-affected surface, the laser-affected surface having one or both of modified dimensions and modified microstructure due to being exposed to the laser-removing of the coating. The laser-affected surface has a depth corresponding to the laser-removing being discontinued based upon the spectroscopic analyzing of the laser-induced plasma formed from the laser-removing.

The present application discloses a method of determining one or more fuel characteristics of an aviation fuel suitable for powering a gas turbine engine of an aircraft. The method comprises: determining, during use of the gas turbine engine, one or more exhaust content parameters by performing a sensor measurement on an exhaust of the gas turbine engine; and determining one or more fuel characteristics of the fuel based on the one or more exhaust parameters. Also disclosed is a fuel characteristic determination system, a method of operating an aircraft, and an aircraft.