2 edition of Experimental characterization of gas turbine emissions at simulated flight altitude conditions found in the catalog.
Experimental characterization of gas turbine emissions at simulated flight altitude conditions
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|
the airstart test program, simulated altitude conditions were selected fron windnilllng maps of each engine; these maps are shown in References Performance tests were conducted at four simulated power settings. Rig test conditions are shown in Table 1. For the FlOO and TF30 rigs these settings corresponded to idle, cruise, takeoff and dash. Engine efficiency is directly linked to the amount of harmful emissions produced. Modelling of gas turbine engines needs to be improved in order to reduce these emissions. The purpose of this study is to model the engine using two outputs: the thrust, which is the force moving the aircraft forward, and the fuel flow used to produce the thrust.
Higher operating efficiencies, fewer pollutant emissions, and low capital investment have made gas turbines a dominant technology for new power generating capacity in the U.S. and worldwide. This book offers gas turbine users and manufacturers a valuable resource to help them sort through issues associated with combustion instabilities. A turbine engine does not work in outer space because there is no surrounding air. For a gas turbine engine, the accelerated gas, or working fluid, is the jet exhaust. Most of the mass of the jet exhaust comes from the surrounding atmosphere. Most modern, high speed passenger and military aircraft are powered by gas turbine engines. Because gas.
Experimental investigations into high-altitude relight of a gas turbine. Realistic operating conditions are simulated in a ground-based test facility. The application of laser diagnostics presents particular difficulties due to the large quantities of liquid fuel that impinge on the combustor walls during relight. Experimental. Gas and Aerosol Chemistry of Commercial Aircraft Emissions Measured in the NASA EXCAVATE Experiment 29 Sulfur (VI) in the simulated internal flow of an aircraft gas turbine engine: first measurements during the PartEmis project 30 Emission of Volatile and Non-Volatile Ultrafine Particles from a Combustion Source During PARTEMIS
way forward for community development organisations in Northern Ireland.
A glossary of terms used in parapsychology
5-minute Christmas stories
Geological, mining and metallurgical sampling
Hagar H/helgas Reven
Modern sculpture in Belgium.
Colorado snow-avalanche area studies and guidelines for avalanche-hazard planning.
Get real money for college
A History of French Passions
Grund Lutheran Church
International narcotics trafficking
Sino Soviet Intervention in Africa
Experimental Characterization of Gas Turbine EmiSsions at Simulated Flight Altitude Conditions R. Howard ct al Sverdrup Technology Inc., AEDC Group September' Final Report for Period January to April E t:l O t National Aeronautics and Space Administration". Experimental characterization of gas turbine emissions at simulated flight altitude conditions [microform]: final report for period January to April / R.P.
Howard et al Arnold Engineering Development Center, Air Force Materiel Command, U.S. Air Force ; National Technical Information Service, distributor [Tullahoma], Tenn. [Springfield, Va. 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. Experimental investigations into high-altitude relight of a gas turbine.
View / Open Files. (PDF, 6Mb) Authors. Read, Robert William. Date Experimental investigations into high-altitude relight of a gas turbine (Doctoral thesis).
Realistic operating conditions are simulated in a ground-based test facility. The. nal gas turbine emission control methods — lean head end liners and water/steam injection — will be covered in this paper. In the early s when emission controls were originally introduced, the primary regulated gas turbine emission was NO x.
For the relative-ly low levels of NO x reduction required in the. This book compiles the key scientific and technological knowledge associated with gas turbine emissions into a single authoritative source.
The book has three sections: the first section reviews major issues with gas turbine combustion, including design approaches and constraints, within the context of emissions. Experimental Characterization of Gas Turbine Emissions at Simulated Flight Altitude Conditions.
Technical Report AEDC-TR, USAF Arnold Engineering Development Center, Arnold AFB, Tennessee. Miake-Lye, R.C., W.J. Dodds, D.W. Fahey, C.E. Kolb, and S.R. Langhoff. Gas Turbine Fuel System and Combustion Study with High Temperature Fuel Injection.
Experimental Characterization of the Near-Wall Plasma in a 6-kW Hall Thruster and Comparison to Simulation. Combustion Dynamics and Emissions Characterization for a Gas Turbine Combustor burning Methane and Propane. Bassam Abdelnabi, Jun Cai.
Experimental characterization of gas turbine emissions at simulated flight altitude conditions. Final report, January April Technical Report Howard, R P ; Wormhoudt, J C ; Whitefield, P D.
R.P. Howard, Editor, Experimental Characterization of Gas Turbine Emissions at Simulated Flight Altitude Conditions, AEDC-TR, 6. Instruction Leaflet /TE, Cascade Impactor, Casella/London, BGI Incorporated, Waltham Mass."Microphysicsof CloudsandPrecipitation",D.
Reidal Publishing,A gas turbine, also called a combustion turbine, is a type of continuous and internal combustion main elements common to all gas turbine engines are: an upstream rotating gas compressor; a combustor; a downstream turbine on the same shaft as the compressor.; A fourth component is often used to increase efficiency (on turboprops and turbofans), to convert power into .WORKED EXAMPLE FOR CALCULATING THE PERFORMANCE OF A GAS TURBINE Step Find the compressor conditions The starting conditions for iterating the compressor variables are, C pc = γ c = −× = T 1 = K T 2e = K, found from Step 4 [step ] The average value of T 1 and T 2e is K.