Author: B. C. SchleinPublisher:
ISBN:
Category : Airplanes, Military
Languages : en
Pages : 0
Book Description
Development of a Dual Fuel Injector for a Gas Turbine Combustor
Author: B. C. SchleinPublisher:
ISBN:
Category : Airplanes, Military
Languages : en
Pages : 0
Book Description
Development of a Dual-fuel Injection System for Lean Premixed Industrial Gas Turbines
Author: Luke H. CowellPublisher:
ISBN:
Category :
Languages : en
Pages : 0
Book Description
Presented at the International Gas Turbine and Aeroengine Congress &Exhibition Birmingham, UK - June 10-13, 1996.
Design and Development of a Porous Injector for Gaseous Fuels Injection in Gas Turbine Combustor
Author: Non MeeboonPublisher:
ISBN:
Category :
Languages : en
Pages : 113
Book Description
A novel porous injector is designed for injection of gaseous fuel in land based gas turbine combustors. The injector is tested at atmospheric conditions at Combustion Research Laboratory, University of Cincinnati. In the present study, seven injector configurations are tested for mixing quality, LBO limits and emissions. For mixing studies, the CO2 technique is adopted to evaluate the fuel-air mixing under atmospheric conditions of the porous injector. The experiments are carried out at 4% pressure drop condition across the injector. The CO2 concentrations are converted to fuel mass fractions for the comparison. A comparison between the top/bottom injections, center/no center injection and 7/30 micron porous tubes show that these configurations do not impact the fuel-air mixing distribution. PIV measurements are carried out in non-reacting as well reacting conditions. Velocity profiles are obtained at a 1%-4% pressure drop condition. The experiments are carried out with and without combustor. A weak outer recirculation zone is observed downstream of the injector in the combustor. The velocity profiles are same at the exit plane of the injector with and without combustor. The velocity decreases gradually along the combustor. The ignition and lean blow out limit are observed to increase as the pressure drop increases. The flame liftoff distance is found to increase as the pressure drop increases. The NO, CO, and O2 emissions are evaluated at the downstream of the porous injector at 6" from the entrance of the combustor. The results show that the NOx emissions are ~ 7 ppm @ 15% O2.
Droplets and Sprays
Author: Saptarshi BasuPublisher: Springer
ISBN: 9811074496
Category : Technology & Engineering
Languages : en
Pages : 433
Book Description
This book focuses on droplets and sprays relevant to combustion and propulsion applications. The book includes fundamental studies on the heating, evaporation and combustion of individual droplets and basic mechanisms of spray formation. The contents also extend to the latest analytical, numerical and experimental techniques for investigating the behavior of sprays in devices like combustion engines and gas turbines. In addition, the book explores several emerging areas like interactions between sprays and flames and the dynamic characteristics of spray combustion systems on the fundamental side, as well as the development of novel fuel injectors for specific devices on the application side. Given its breadth of coverage, the book will benefit researchers and professionals alike.
Industrial Sprays and Atomization
Author: Ghasem G. NasrPublisher: Springer Science & Business Media
ISBN: 1447138163
Category : Technology & Engineering
Languages : en
Pages : 515
Book Description
An extensive critical compilation of the wide range of manufacturing processes that involve the application of spray technology, this book covers design of atomizers as well as the performance of plant and their corresponding spray systems. The needs of practising engineers from different disciplines: project managers, and works, maintenance and design engineers are catered for. Of interest to researchers in the field of liquid sprays, the book includes outlines of the contemporary and possible future research and challenges in the different fields of application and deals with: • sprays and their production; • sprays in industrial production processes; • processes involving vaporisation and cooling or cleaning of gases; • spray-surface impact processes; • fuel sprays for fixed plant; • spraying of hot surfaces for steel making and other metals; • spraying of molten metals. Guidance is given for the analysis and interpretation of experimental data obtained using different measurement techniques.
Army Research and Development
Author: DEVELOPMENT AND DEMONSTRATION OF AN ULTRA LOW NOx COMBUSTOR FOR GAS TURBINES.
Author: NEIL K. MCDOUGALD.Publisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
Alzeta Corporation has developed surface-stabilized fuel injectors for use with lean premixed combustors which provide extended turndown and ultra-low NOX emission performance. These injectors use a patented technique to form interacting radiant and blue-flame zones immediately above a selectively-perforated porous metal surface. This allows stable operation at low reaction temperatures. This technology is being commercialized under the product name nanoSTAR. Initial tests demonstrated low NOX emissions but, were limited by flashback failure of the injectors. The weld seams required to form cylindrical injectors from flat sheet material were identified as the cause of the failures. The approach for this project was to first develop new fabrication methods to produce injectors without weld seams, verify similar emissions performance to the original flat sheet material and then develop products for microturbines and small gas turbines along parallel development paths. A 37 month project was completed to develop and test a surface stabilized combustion system for gas turbine applications. New fabrication techniques developed removed a technological barrier to the success of the product by elimination of conductive weld seams from the injector surface. The injectors demonstrated ultra low emissions in rig tests conducted under gas turbine operating conditions. The ability for injectors to share a common combustion chamber allowing for deployment in annular combustion liner was also demonstrated. Some further development is required to resolve integration issues related to specific engine constraints, but the nanoSTAR technology has clearly demonstrated its low emissions potential. The overall project conclusions can be summarized: (1) A wet-laid casting method successfully eliminated weld seams from the injector surface without degrading performance. (2) Gas turbine cycle analysis identified several injector designs and control schemes to start and load engines using nanoSTAR technology. A mechanically simple single zone injector can be used in Solar Turbine's Taurus 60 engine. (3) Rig testing of single monolithic injectors demonstrated sub 3 ppmv NOX and sub 10 ppmv CO and UHC emissions (all corrected to 15% O2) at Taurus 60 full-load pressure and combustion air inlet temperature. (4) Testing of two nanoSTAR injectors in Solar Turbine's sector rig demonstrated the ability for injectors to survive when fired in close proximity at Taurus 60 full load pressure and combustion air inlet temperature. (5) Sector rig tests demonstrated emissions performance and range of operability consistent with single injector rig tests. Alzeta has committed to the commercialization of nanoSTAR injectors and has sufficient production capability to conclude development and meet initial demand.
ASME Technical Papers
Author: Publisher:
ISBN:
Category : Mechanical engineering
Languages : en
Pages : 428
Book Description
Development of Fuel Injectr System for Micro Gas Turbine Combustor
Author: Noor Zaliza Zainal AbidinPublisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
Author: Robert R. Tacina