This project will develop models to predict the physical characteristics and behaviors of alternative jet fuels within jet engines. Of specific interest is the characterization of primary and secondary breakup of the liquid fuel into droplets and the subsequent evaporation.
Industrial Partners:
- Williams International
- Honeywell
- Pratt & Whitney/United Technologies Research Center
Federal Agencies:
- Air Force Office of Scientific Research
- National Aeronautics and Space Administration
- Defense Logistics Agency – Energy
- NavAir
- Army Research Laboratory
- National Institute of Standards and Technology
International Partners
- National Research Council (Canada)
- DLR (Germany)
- University of Sheffield (UK)
ASCENT Committee Member
- CAAFI
- Boeing
- Shell
- Gevo
Annual Reports
- 2015 Annual Report – 029A
- 2015 Annual Report – 029B
- 2016 Annual Report
- 2017 Annual Report
- 2018 Annual Report – 029A
Participants
Lead Investigators
Program Managers
Publications
- Formulation of optimal surrogate descriptions of fuels considering sensitivities to experimental uncertainties
- Large Eddy Simulation of Pilot Stabilized Turbulent Premixed CH4+Air Jet Flames
- Comparison of Premixed Flamelet Generated Manifold Model and Thickened Flame Model for Bluff Body Stabilized Turbulent Premixed Flame
- Lean blow-out (LBO) computations in a gas turbine combustor
- Numerical Simulation of Flow Distribution in a Realistic Gas Turbine Combustor
- A Numerical Study of Flame Characteristics during Lean Blow-Out in a Gas Turbine Combustor
- Large-Eddy Simulations of Fuel Effects on Gas Turbine Lean Blow-out
- Group contribution method for multicomponent evaluation with application to transportation fuels
- The role of preferential evaporation on the ignition of multicomponent fuels in a homogeneous spray/air mixture
- Large-Eddy Simulation of Fuel Effect on Lean Blow-out in Gas Turbines
- Spray Measurements at Elevated Pressures and Temperatures Using Phase Doppler Anemometry
- High-Fidelity Simulations of Fuel Injection and Atomization of a Hybrid Air-Blast Atomizer
- Effect of Aviation Fuel Type and Fuel Injection Conditions on Non-reacting Spray Characteristics of Hybrid Air Blast Fuel Injector