THE AMERICAN SOCIETY OF MECHANICAL ENGINEERS

DECS digital engine control system DERV Diesel Engine Road Vehicle (fuel) An F402-RR-406A (Pegasus) engine has been die degrees of freedom for error/residuals, subjected to extensive sea-level and altitude i.e. (n-2) for a linear fit and (n-3) for operation on a wide range of viable emergency a quadratic fit fuels. Sea-level main engine starting was DFM Diesel Fuel Marine successful for all six fuels and windmilling DMPS (TSI) Differential Mobility Particle Sizer altitude relight tests were equally flawless, even DNB dry, no bleed outside the flight envelope. Cold soak sea-level DZR4 dilution zone radiometer reading at starting was achieved with DFM of viscosities up position R4, converted to 'equivalent to 12 centistokes. Clear inter-relationships wide-angle' radiative flux units, MW/m 2 between combustor metal temperatures, primary zone EAA (TSI) Electrical Aerosol Analyzer flame radiation and optically measured exhaust EICO emission index for CO, g/kg fuel Smoke Numbers demonstrate a common dependence of EIJHC emission index for unburned hydrocarbons, these parameters upon the indeterminable primary g/kg fuel zone soot concentration. Correlations against EXP exponent (power of 10) fuel properties illustrate the dominance of fuel far combustor fuel/air ratio chemistry over physical properties, even with FIA fluorescence indicator adsorption respect to changes in carbon monoxide and unburned GTS gas turbine starter hydrocarbon emissions (and hence combustion h (fuel) hydrogen content, % by weight inefficiency) at low power. The degrees of He (fuel) net heat/enthalpy of combustion, premixing and prevaporisation within the MJ/kg Rolls-Royce 'vaporiser' fuel injector are HPLC high performance liquid chromatography considered responsible for the diminished HSU Hartridge Smoke Units significance of physical properties relative to ISA International Standard Atmosphere influences upon conventional fuel atomiser LCF low cycle fatigue behaviour. MDR Motor Diesel Referee (Grade) n number of data points NOMENCLATURE NAPC (US) Naval Air Propulsion Center (Trenton, New Jersey) a constant coefficient NLD normal lift, dry APU auxiliary propulsion unit NLW normal lift, 'wet' (with water injection) ASTM American Society for Testing and Materials NMR nuclear magnetic resonance b constant coefficient No.2 Number 2 heating oil BDC bottom, dead centre P3 combustor inlet (total) pressure, psi(a) c constant coefficient (1 psi = 6.89476 kPa) C (exhaust smoke) DMPS particle total psi(a) pounds (force) per square inch (absolute) concentration PZR primary zone radiative flux, in d (exhaust smoke) DMPS particle mean 'equivalent wide-angle' units, MW,/m 2 diameter,Llm PZR1, primary zone radiometer readings at D20 (exhaust smoke) particle area (mean) PZR2, positions R1, R2 and R3, respectively diameter, Um (Eq. (15)) PZR3 converted to 'equivalent wide-angle' D32 (exhaust smoke) particle volume-surface units, MW/m 2 (mean) diameter, i.e. SMD, urn (Eq. (14)) R correlation coefficient Presented at the Gas Turbine and Aeroengine Congress and Exposition—June 11-14. 1990—Brussels, Belgium Copyright © 1990 by ASME Downloaded From: https://proceedings.asmedigitalcollection. asme.org on 04/15/2019 Terms of Use: http://www.asme.org/about-asme/terms-of-use R 2 coefficient of determination R 2 coefficient of determination adjusted for number of degrees of freedom (to allow for a small number of data points), using the relationship: (1 -R2 ) = (1-R 2 ). (n 1) dfe Rl,R2, positions of primary zone radiometers R3 (Figs. 3-4) R4 position of dilution zone radiometer (Figs. 3-4) RCS reaction control system SAE Society of Automotive Engineers SLS sea-level, static SMD Sauter mean diameter (D32) SN (exhaust, SAE) Smoke Number sp (fuel) smoke point, mm SwRI Southwest Research Institute (San Antonio, Texas) T3 combustor inlet (total) temperature, K TB,G, combustor liner temperatures (see Subscripts) tar (fuel) total aromatics content TDC top, dead centre TSI Thermo-Systems Inc. UHC unburned hydrocarbons UK United Kingdom VIFF vectoring in forward flight V/STOL vertical/short take-off and landing /j Blazowski parameter, expressing liner temperature sensitivity to fuel property changes \T combustor liner temperature increment, K q c combustion efficiency (measured by exhaust gas analysis) % (100-q)combustion inefficiency (measured by exhaust gas analysis), % Subscripts B measured at primary zone position B (Fig. 3), for outer liner temperature G measured at primary zone position G (Fig. 3), for inner liner temperature h calculated for a 1% change in fuel hydrogen content (h) idle corresponding to the F402-RR-406A ground idle rating l liner ( ref. liner, with a reference fuel and at the datum engine condition (ISA NLD) N calculated on a number basis, e.g. per cc for concentration C S calculated on a surface area basis, e.g. (Um) 2 /cc for concentration C V calculated on a volume basis, e.g. (Um) 3/cc for concentration C 3 datum combustor inlet at the datum engine condition