Thrust Spoiler/Reverser System for a Low-Cost Expendable Turbojet Engine

摘要

During the performance period, a heavy-wall ground-test thrust spoiler/reverserwas designed, fabricated and tested on a Sundstrand TJ-90 expendable turbojet engine. Maximum forward corrected thrust attained was 91.8 lbs. and maximum reverse corrected thrust was 68.2 lbs. Thrust from a circular calibration nozzle under the same conditions was 95.4 lbs. The reverser consisted of bifurcated Hastelloy-X exhaust duct with machined Hastelloy-X nozzles and deflectors at each exit. The deflectors were driven by an electric servo actuator through a rod-end bearing linkage assembly. Actuation time from full forward to full reverse was 0.5 seconds. At the conclusion of the program, a layout of a flight-weight reverser was created.