Aircraft gas turbine performance and efficiency are related to airfoil tip clearance. The possibility has been considered to obtain optimum performance and efficiency by reducing clearance to a safe minimum with the aid of a closed-loop tip clearance control system, which utilizes a tip clearance sensor. The use of optical sensing methods appears to represent a potential solution to the tip clearance measurement problem. Principles of sensor operation are discussed along with dimensional considerations and diffraction limitations. A description is presented of the study of the feasibility of a certain sensor, taking into account the test rig system, the optical components, and the mounting tube. Attention is also given to the operation of the feasibility-study sensor, performance estimations, the optical fiber bundle, light beam refraction, and aspects of aircraft engine implementation.


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    Title :

    Optical tip clearance sensor for aircraft engine controls


    Contributors:

    Conference:

    Joint Propulsion Conference ; 1982 ; Cleveland, OH


    Publication date :

    1982-06-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English




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