Aircraft gas turbine engine backbone deflection thermal control

摘要

A gas turbine engine thermal backbone deflection control apparatus to counter the effects of backbone bending due to nacelle aerodynamic, thrust, and maneuver loads by introducing a controlled backbone counter-bending moment by applying an uneven temperature or thermal field around the backbone to induce controlled compression and/or tensioning forces in the backbone or casing between axially spaced apart frames connected by the backbone. One embodiment of the invention provides for flowing thermal control air along an axially and circumferentially sector of the engine casing. The thermal backbone deflection control apparatus is controlled by the engines digital electronic control system using input signals generated by engine thrust load, inlet moment load sensors and/or blade tip clearance sensors.