Accession Number:

AD1032042

Title:

Flow Field Dynamics in a High-g Ultra-Compact Combustor

Descriptive Note:

Technical Report,01 Sep 2013,22 Dec 2016

Corporate Author:

AIR FORCE INSTITUTE OF TECHNOLOGY WRIGHT-PATTERSON AFB OH WRIGHT-PATTERSON AFB United States

Personal Author(s):

• Cottle,Andrew E

Report Date:

2016-12-01

Pagination or Media Count:

423.0

Abstract:

The Ultra Compact Combustor UCC presents a novel solution to the advancement of aircraft gas turbine engine performance. A high-g UCC design operates by diverting a portion of the axial compressor flow into a circumferential combustion cavity positioned about the engine outer diameter. The circumferential cavity CC provides the necessary residence length and time for combustion within reduced axial lengths furthermore, high rates of centrifugal acceleration termed high-g loading are imposed upon the swirling cavity flow. These high-g conditions are hypothesized to increase flame speed, reduce flame length, and improve lean blow-out performance. Work at AFIT was sponsored by the Air Force Office of Scientific Research to study high-g combustion. This research capitalized on the availability of advanced flow diagnostic data coupled with a computational fluid dynamics CFD model to provide detailed insight into the high-g flow field and combustion dynamics. Results indicated that combustion could be sustained and controlled in a manner suitable for integration into modern gas turbine engine architecture.

Descriptors:

• COMBUSTORS
• computational fluid dynamics
• turbulent mixing
• secondary flow
• burning rate
• dielectric gases
• pressure measurement
• laser induced fluorescence
• flow visualization
• hydrodynamics
• boundary layer
• heat transfer
• chemical reactions
• particle image velocimetry
• laser spectroscopy
• GAS TURBINES

Subject Categories:

• Fluid Mechanics
• Combustion and Ignition

Distribution Statement:

APPROVED FOR PUBLIC RELEASE