by Arnold Engineering Development Center, Air Force Materiel Command, U.S. Air Force, National Technical Information Service, distributor in [Tullahoma], Tenn, [Springfield, Va .
Written in English
|Statement||R.P. Howard et al.|
|Series||NASA technical memorandum -- 112751.|
|Contributions||Howard, R. P., Arnold Engineering Development Center., United States. National Aeronautics and Space Administration.|
|The Physical Object|
Get this from a library! Experimental characterization of gas turbine emissions at simulated flight altitude conditions: final report for period January to April [R P Howard; Arnold Engineering Development Center.; United States. National Aeronautics and Space Administration.; et al]. Experimental Characterization of Gas Turbine Emissions at Simulated Flight Altitude Conditions R P. Howard el al Sverdmp Technology Inc., AE[)C Group Seplember Final Report for Period January to April ' ¢,JE> ¢JC) O ¢.,¢=> O CY> National Aeronau_lce end Space Administration Th._ work was sp_,_sored by NASA through the Atmospheric. Howard, R. P., et al., , “Experimental Characterization of Gas Turbine Emissions at Simulated Flight Altitude Conditions,” AEDC-TR, Arnold Engineering Development Center, Arnold Air Force Base, TN. Cited by: (6) Heland J, Schafer K. Analysis of aircraft exhausts with Fourier-transformed infrared emission spectroscopy, Appl. Opt. 36 () 1 (7) Howard RP Experimental Characterization of Gas Turbine Emissions at Simulated Flight Altitude Conditions, AEDC report TR, Sept.
Experimental Characterization of Gas Turbine Emissions at Simulated Flight Altitude Conditions. as it contributes to achieve higher operating temperature conditions of modern gas turbines, and. (3) Döpelheuer, A.; Lecht, M. Influence of engine performance on emission characteristics. RTO Meeting Proceedings 14; RTO/NATO: Hull, Canada, (4) Experimental Characterization of Gas Turbine Emissions at Simulated Altitude Conditions; AEDC-TR; Arnold Engineering Development Center, Tullahoma, TN, Corber, Andrew, Rizk, Nader, and Chishty, Wajid Ali. "Experimental and Analytical Characterization of Alternative Aviation Fuel Sprays Under Realistic Operating Conditions." Proceedings of the ASME Turbo Expo Turbomachinery Technical Conference and Exposition. Volume 4A: Combustion, Fuels, and Emissions. Oslo, Norway. June 11–15, Although the current mass-based techniques can reliably detect concentrations ∼10 μg/m 3, the advanced gas turbines emit BC mass ∼1 μg/m 3 at some conditions of the standard emissions test cycle (Crayford et al., ). Therefore, the sensitive IPSD technique could provide additional information along the regulatory measurements.
Scimitar engine is a hypersonic hybrid engine designed to propel the LAPCAT A2 aircraft. In this study, a novel exergy and NO x emission-based ecological performance analysis of t. requirement of a gas turbine engine. The performance requirement is mainly determined by the amount of shaft horsepower (s.h.p.) the engine develops for a given set of conditions. The majority of aircraft gas turbine engines are rated at standard day conditions of 59 °F and inches Hg. In this paper, a detailed description of the experimental set-up and some results of the infrared characterization of a micro turbine engine at ground level (having altitude of ~ m AMSL) are. shaft gas turbine is shown in Figure 2. Air enters the axial flow compressor at point 1 at ambient conditions. Since these conditions vary from day to day and from location to location, it is convenient to consider some standard condi-tions for comparative purposes. The standard conditions used by the gas turbine industry are.