Date of Award

9-1-2013

Document Type

Thesis

Degree Name

Master of Science

Department

Department of Aeronautics and Astronautics

First Advisor

Marc D. Polanka, PhD.

Abstract

Previous research has been conducted showing significant benefits on combustion efficiency and stability by creating high centripetally accelerated, also known as g-loaded, combustion environments. Ultra Compact Combustor systems decrease size and weight of the overall engine by burning in a circumferential direction around a hybrid vane row where the high equivalence ratio cavity flow is quick quenched to lean by the core flow. The hybrid vane row integrates the compressor, combustor, and turbine for further length reduction and weight savings. Fuel and air are brought into the cavity and combusted in a high g-loaded environment driven by air injection at an angle tangent to the cavity outer diameter. The Air Force Research Lab and Air Force Institute of Technology have worked previously on compact combustor designs, and a new, high g-loaded, Ultra Compact Combustor has been designed to study flow characteristics in the cavity and core to help understand integration issues with engine systems.

AFIT Designator

AFIT-ENY-13-S-02

DTIC Accession Number

ADA584000

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