Accession Number : ADA301712
Title : Thrust Spoiler/Reverser System for a Low-Cost Expendable Turbojet Engine.
Descriptive Note : Final rept. 23 Jan-10 Sep 93,
Corporate Author : M-DOT INC PHOENIX AZ
Personal Author(s) : Seegers, Bryan J. ; Shreiner, David G.
PDF Url : ADA301712
Report Date : 25 OCT 1993
Pagination or Media Count : 44
Abstract : During the performance period, a heavy-wall ground-test thrust spoiler/reverser was 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.
Descriptors : *LOW COSTS, *SPOILERS, *TURBOJET ENGINES, *THRUST REVERSAL, TIME, REVERSIBLE, NOZZLES, ELECTRIC POWER, CALIBRATION, ACTUATORS, THRUST, SERVOMECHANISMS, ACTUATION, CIRCULAR, CORRECTIONS, DEFLECTORS.
Subject Categories : Economics and Cost Analysis
Jet and Gas Turbine Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE