Small turbine engine augmentor design methodology-Reference-Cited by-同舟云学术

Small turbine engine augmentor design methodology

Published:1982-06-21 Issue: Volume: Page:
ISSN:
Container-title:18th Joint Propulsion Conference
language:
Short-container-title:

Author:

KUHN T.¹,MONGIA H.¹,BRUCE T.¹,BUCHANAN E.²

Affiliation:

1. Garrett Turbine Engine Co., Phoenix, AZ

2. USAF, Wright Aeronautical Laboratories, Wright-Patterson AFB, OH

Publisher

American Institute of Aeronautics and Astronautics

Link

http://arc.aiaa.org/doi/pdf/10.2514/6.1982-1179

Reference11 articles.

1. A Method of Estimating Pressure Loss Across Flame Holders in High Velocity Streams

2. Large augmentor semianalytical design techniques, currently used for estimating combustion efficiency and instability and for the detailed flameholder and spray injection design, are not directly applicable to a cruisemissile augmentor design. A design technique based on the use of semianalytical methods, along with rnultidimensional aerothermal analysis has been described that is applicable for smaller thrust-class engines. Partial validation of the technique has already been achieved using existing data on spray injection and flow characteristics around typical flameholders. This improved technique has been used to design an augmentor for a small gas turbine engine in a thrust class of less than 1000 pounds. Rig demonstration of this augmentor is planned for Phase 111 of this program. Airstreams, AIAA Paper 77-201.

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