Accession Number:

ADA017458

Title:

An Investigation of the Static Thrust Augmentation Capabilities of a Divergent Ejector-Afterburner

Descriptive Note:

Master's thesis

Corporate Author:

AIR FORCE INST OF TECH WRIGHT-PATTERSONAFB OH SCHOOL OF ENGINEERING

Personal Author(s):

Report Date:

1975-06-01

Pagination or Media Count:

115.0

Abstract:

The effects on static thrust augmentation and mass entrainment of various divergent ejector-afterburner configurations were investigated. Static tests were conducted using a gaseous oxygenhydrogen sonic rocket as the primary gas generator. Configurations included various length mixing ducts, two different size diffusers, burn ducts, and secondary nozzles. Oxydizer-to-fuel mixture ratio was varied from .3 to 1.5 at 80 psia chamber pressure. Results indicated maximum static thrust augmentation 220 when the relatively unmixed primary and secondary streams were diffused immediately after the secondary inlet and then allowed to complete mixing in a constant area duct, for a total afterburner length of about six inlet diameters.

Subject Categories:

  • Guided Missiles
  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE