Accession Number:

ADA101595

Title:

Small Turbine Engine Augmentor. Phase 1. Preliminary Design Studies of Afterburner and Duct-Burner Configurations

Descriptive Note:

Interim technical rept. 1 Aug-29 Oct 1980

Corporate Author:

GARRETT TURBINE ENGINE CO PHOENIX AZ

Personal Author(s):

Report Date:

1981-03-01

Pagination or Media Count:

47.0

Abstract:

Several candidate afterburner and duct-burner concepts were evaluated. The evaluation procedure included assessing engine and augmentor performance when integrated with airframes and mission data available from ATCM potential contractors. From the candidates analyzed, two configurations were chosen for further design evaluation. Of the several augmentor concepts screened, the conventional flameholder with mixer-nozzle and the partial-swirl augmentor were determined to produce the highest combustion efficiency with the least impact on the size or performance of the core engine. These two designs were therefore selected for detail analysis. Two engines were evaluated for use in augmented cruise missiles. The lower-bypass-ratio engine was selected because of its smaller diameter, similarity to the Boeing ALCM-L engine, and greater suitability for augmentation. The effect of using JP-10 and RJ-6 fuels was predicted to be small, but carbon-slurry fuel will require extensive modifications to the fuel manifold.

Subject Categories:

  • Guided Missiles
  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE