Physics-Based Control Technology for Augmentor Screech Suppression

Award Information
Agency:
Department of Defense
Branch
Air Force
Amount:
$749,870.00
Award Year:
2011
Program:
STTR
Phase:
Phase II
Contract:
FA9550-11-C-0001
Award Id:
n/a
Agency Tracking Number:
F08B-T15-0128
Solicitation Year:
2008
Solicitation Topic Code:
AF08-BT15
Solicitation Number:
2008.B
Small Business Information
9950 Wakeman Drive, Manassas, VA, -
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
N
Duns:
604717165
Principal Investigator:
JamesSisco
Propulsion Engineer
(617) 500-4835
jsisco@aurora.aero
Business Contact:
DianaEichfeld
Contracts Manager
(703) 396-6329
deichfeld@aurora.aero
Research Institute:
University of Maryland
Marcine Snyder
ORAA
3112 Lee Building
College Park, MD, 20742-
(301) 405-6177

Abstract
ABSTRACT: High frequency combustion instabilities in gas turbine thrust augmentors (called screech) are detrimental to performance and limit operational flexibility, but are unavoidable due to the nature of augmentor operation and design. Present approaches to screech suppression via passive control provide acoustic damping over limited bandwidth, while active control methods are impractical for flight applications due to system weight. Building on progress in Phase I, in this Phase II effort an improved flame dynamics model will be developed to describe flame-vortex dynamics in the vicinity of a bluff body flameholder. The model will be coupled to combustor multi-dimensional mean flow and acoustics via a commercial finite element solver, COMSOL Multiphysics, and validated against detailed experimental data obtained from two, two-dimensional combustors operating at afterburner-like dilatation ratios containing dissimilar flameholders: a backward facing step and a v-gutter bluff body. The model will be extended to a notional three-dimensional combustor geometry containing multiple bluff bodies to illustrate its capabilities in an afterburner-like environment. This technology will not only be an enabler for thrust augmentors, but will also find application in other combustion systems susceptible to dynamic instability. BENEFIT: The flame dynamic model and combustor stability analysis tool developed through this effort will have direct application to existing and planned thrust augmentor systems used in both military and commercial gas turbine propulsion systems. As such it would be of interest to government agencies such as the Air Force and Navy as well as large aircraft engine manufacturers such as Pratt & Whitney, General Electric, and Rolls Royce. Since the technology will be physics based, key dynamic models may be revisited and/or new models developed to adapt the control technology to other combustion systems which are susceptible to combustion instability such as aircraft and stationary gas turbine combustors, liquid rockets, boilers, and furnaces. This opens the technology to application over a wide range of military and commercial markets.

* information listed above is at the time of submission.

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