NTRS - NASA Technical Reports Server

Back to Results
Alternative Bio-Derived JP-8 Class Fuel and JP-8 Fuel: Flame Tube Combustor Test Results Compared using a GE TAPS Injector ConfigurationThis paper presents results from tests in a flame tube facility, where a bio-derived alternate fuel was compared with JP-8 for emissions and general combustion performance. A research version of General Electric Aviation (GE) TAPS injector was used for the tests. Results include combustion efficiency from gaseous emission measurements, 2D planar laser-based imaging as well as basic flow visualization of the flame. Four inlet test conditions were selected that simulate various engine power conditions relevant to NASA Fundamental Aeronautics Supersonics Project and Environmentally Responsible Aviation Program. One inlet condition was a pilot-only test point. The other three inlet conditions incorporated fuel staging via a split between the pilot and main circuits of either 10%/90% or 20%/80%. For each engine power condition, three fuel mixes were used: 100% JP-8; 100% alternative; and a blend of the two, containing 75% alternative. Results for the inlet cases that have fuel split between pilot and main, indicate that fuel from the pilot appears to be evaporated by the time it reaches the dome exit. Main circuit liquid evaporates within a downstream distance equal to annulus height, no matter the fuel. Some fuel fluorescence images for a 10%/90% fuel staging case show a distinct difference between JP-8 and bio-derived fuel. OH PLIF results indicate that OH forms in a region more centrally-located for the JP-8 case downstream of the pilot, in its central recirculation region (CRZ). For the bio-derived Hydrotreated Renewable Jet (HRJ) fuel, however, we do not see much OH in the CRZ. The OH image structure near the dome exit is similar for the two fuels, but farther downstream the OH in the CRZ is much more apparent for the JP-8 than for the alternate fuel. For all conditions, there was no discernable difference between fuel types in combustion efficiency or emissions.
Document ID
Document Type
Conference Paper
Hicks, Yolanda R.
(NASA Glenn Research Center Cleveland, OH United States)
Tedder, Sarah A.
(NASA Glenn Research Center Cleveland, OH United States)
Anderson, Robert C.
(NASA Glenn Research Center Cleveland, OH United States)
Date Acquired
January 27, 2017
Publication Date
July 25, 2016
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
Meeting Information
AIAA/SAE/ASEE Joint Propulsion Conference(Salt Lake City, UT)
Funding Number(s)
WBS: WBS 338881.
Distribution Limits
Work of the US Gov. Public Use Permitted.
gas turbine combustors
optical diagnostics
alternative fuels
No Preview Available