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.
Optical tip clearance sensor for aircraft engine controls
Joint Propulsion Conference ; 1982 ; Cleveland, OH
01.06.1982
Aufsatz (Konferenz)
Keine Angabe
Englisch
Autothermic piston controls clearance
Engineering Index Backfile | 1936
|Engine Controls for Integrated Aircraft Systems
Emerald Group Publishing | 1986
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