A gas turbine engine having an optical imaging system with a housing configured for mounting to a wall of the turbine engine, a hollow probe extending from the housing and having a longitudinal axis, and an image receiving device at an end of the hollow probe configured to receive at least one of a perspective or image.

A measuring probe head having a housing, which defines a receiving space and at least one coolant fluid supply channel fluidically connected thereto, and at least one sensor which is received, or is capable of being received, in the receiving space, wherein at least one partial region of the housing enclosing the receiving space has a porosity which defines a plurality of coolant fluid passage openings.

A device for measuring surface-temperature of a turbine blade, the device including a probe having a front-end mirror for receiving infrared radiation of a surface on the blade, a collimation lens for refracted the infrared radiation, a PD detector to receive the infrared radiation, and a focal-length servo; and a radial-scanning servo connected to the probe. The front-end mirror, the collimation lens, and PD detector are disposed along the optical axis of the collimation lens. The focal-length servo is adapted to move the collimation lens along the optical axis of the collimation lens. The radial-scanning servo is adapted to move the probe along the optical axis of the collimation lens. The device of the invention is capable of accurately targeting a particular point on the blade having an irregular shape for temperature measurement to accurately detect the temperature distribution on the surface of the blade.

A method of collecting radiation information of a turbine blade, the method including: 1) collecting a radiated light from the surface of the turbine blade, analyzing the radiated light using a spectrometer to calculate compositions and corresponding concentrations of combustion gas; 2) calculating an absorption coefficient of the combustion gas at different concentrations; 3) calculating a total absorption rate of the combustion gas at different radiation wavelengths under different concentrations of component gases; 4) obtaining a relationship between the radiation and a wavelength; 5) finding at least 3 bands with a least gas absorption rate; 6) calculating a distance between a wavelength of a strongest radiation point of the turbine blade and the center wavelength, and selecting three central wavelengths closest to the wavelength with the strongest radiation; and 7) acquiring radiation data of the turbine blade in the windows obtained in 6).

Provided is an optical sensor directed into a combustion chamber is used to selectively sense a predefined spectral range of an optical spectrum for different light paths running through the combustion chamber to measure a gas temperature distribution in the combustion chamber. A spectral intensity is determined for each spectral range and associated with an item of light path information which identifies the light path in question. The spectral intensities determined and and the associated items of light path information are fed as input data to a machine learning routine which is trained to reproduce spatially resolved training temperature distributions. Output data from the machine learning routine are then output as the gas temperature distribution.

Evaluation method and system for a lightning protection system of a wind turbine with blades, the lightning protection system including a down conductor connected to earth and to each blade by conductor plates embedded in the corresponding blade. The method is configured for determining the quality of the connections between the conductor plates and the blade thereof and includes injecting direct current between two conductor plates of one and the same blade, a flow of current being generated through the segment of the blade comprised between both conductor plates, measuring the voltage at measurement points of the segment, comparing the voltages to one another, and determining the quality of the connections between the conductor plates and the blade depending on the result of the comparison.

A method of forming a film cooling hole in a component having an internal surface and an external surface is disclosed herein that includes forming the component with a first feature on the external surface, measuring a geometry of the external surface to determine a first placement of the first feature, and drilling the film cooling hole through the component at the first placement.

A thermal imaging system for use in maintaining a turbine assembly includes a case, a single pixel detector positioned within the case, at least one optical transportation device, and a prism. The optical transportation device is coupled to the case and configured to direct electromagnetic radiation to the single pixel detector. The prism is coupled to the optical transportation device and configured to direct electromagnetic radiation into the optical transportation device and to the single pixel detector. At least the prism and the optical transportation device are inserted into the turbine assembly and the single pixel detector acquires images of the turbine assembly.

A method of imaging a turbine engine component with a first surface and a second surface that is spaced from the first surface. The turbine engine component includes a plurality of holes with inlets formed in the second surface or interior that are fluidly coupled to outlets formed in the first surface or exterior. The method includes determining at least one fluid frequency, determining at least one sampling frequency, and pulsing fluid through at least a portion of the interior of turbine engine component while imaging the turbine engine component.

A temperature detecting device for a gas turbine power plant is provided with at least one optical probe configured to detect a parameter indicative of a temperature and with at least one capsule configured to define a camera inside which the optical probe is housed.