Optical probe for light barrier for turbine for gas turbine plant for aircraft, has transfer location aligning light transfer surface to end of optical fiber, and optical component for optical coupling of transfer location with spatial area

摘要

The probe (22) has a hollow shaft (28) with a section (30) formed in a turbo-machine and another section (40) provided within a flow channel. A transfer location (34) is provided at the former section and aligns a light transfer surface to an end of an optical fiber or of an opto-electronic transducer or electro-optic transducer. The optical fiber optically couples the probe with a device. An optical component i.e. mirror (42), is provided at the latter section for optical coupling of the transfer location with a spatial area outside the shaft. The optical component comprises a mirror surface. Independent claims are also included for the following: (1) a method for providing light for optical measurement in a flow channel (2) a method for detecting light for optical measurement in a flow channel in a turbine.