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

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.

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Document Details

Document Type
Technical Report
Publication Date
Oct 25, 1993
Accession Number
ADA301712

Entities

People

  • Bryan J. Seegers
  • David G. Shreiner

Tags

DTIC Thesaurus Topics

  • Actuators
  • Assembly
  • Calibration
  • Deflectors
  • Engines
  • Expendable
  • Jet Aircraft
  • Mechanical Equipment
  • Spoilers
  • Turbojet Engines

Fields of Study

  • Physics

Readers

  • Electrical Engineering
  • Rocket Propulsion.
  • Software Engineering