scholarly journals Swirl-Can Combustor Performance to Near-Stoichiometric Fuel-Air Ratio

1976 ◽  
Author(s):  
L. A. Diehl ◽  
J. A. Biaglow
Keyword(s):  
Air Temperature ◽  
Combustion Efficiency ◽  
Oxides Of Nitrogen ◽  
Module Design ◽  
Air Temperatures ◽  
Nitrogen Emission ◽  
Unburned Hydrocarbons ◽  
Exit Temperature ◽  
And Performance ◽  
Emissions And Performance

Emissions and performance characteristics were determined for two full-annulus swirl-can modular combustors operated to near-stoichiometric fuel air ratios. The purposes of the tests were to obtain stoichiometric data at inlet-air temperatures up to 894 K and to determine the effect of module number by investigating 120 and 72 module swirl-can combustors. The maximum average exit temperature obtained with the 120-module swirl-can combustor was 2465 K with a combustion efficiency of 95 percent at an inlet-air temperature of 894 K. The 72-module swirl-can combustor reached a maximum average exit temperature of 2306 K with a combustion efficiency of 92 percent at an inlet-air temperature of 894 K. At a constant inlet air temperature, maximum oxides of nitrogen emission index values occurred at a fuel-air ratio of 0.037 for the 72-module design and 0.044 for the 120-module design. The combustor average exit temperature and combustion efficiency were calculated from emissions measurements. The measured emissions included carbon monoxide, unburned hydrocarbons, oxides of nitrogen, and smoke.

scholarly journals Emissions and Performance of Catalysts for Gas Turbine Catalytic Combustors

1977 ◽  
Author(s):  
D. N. Anderson
Keyword(s):  
Gas Turbine ◽  
Combustion Efficiency ◽  
Temperature Pattern ◽  
Turbine Engine ◽  
Reference Velocity ◽  
Test Conditions ◽  
Exit Temperature ◽  
And Performance ◽  
Catalytic Combustor ◽  
Emissions And Performance

Three noble-metal monolithic catalysts were tested in a 12-cm-dia combustion test rig to obtain emissions and performance data at conditions simulating the operation of a catalytic combustor for an automotive gas turbine engine. Tests with one of the catalysts at 800 K inlet mixture temperature, 3 × 105 Pa (3 atm) pressure, and a reference velocity (catalyst bed inlet velocity) of 10 m/sec demonstrated greater than 99 percent combustion efficiency for reaction temperatures higher than 1300 K. With a reference velocity of 25 m/sec the reaction temperature required to achieve the same combustion efficiency increased to 1380 K. The exit temperature pattern factors for all three catalysts were below 0.1 when adiabatic reaction temperatures were higher than 1400 K. The highest pressure drop was 4.5 percent at 25 m/sec reference velocity. Nitrogen oxides emissions were less than 0.1 g NO2/kg fuel for all test conditions.

scholarly journals EFFECT OF INLET AIR TEMPERATURE ON COMBUSTION, PERFORMANCE AND EMISSIONS OF GASOLINE DIRECT INJECTION (GDI) ENGINE FUELLED BY LPG FUEL

2021 ◽  
Vol 21 (4) ◽  
pp. 289-301
Author(s):  
Mohanad Aldhaidhawi ◽  
Oras Khudhayer Obayes ◽  
Muneer Najee
Keyword(s):  
Fuel Consumption ◽  
Air Temperature ◽  
Direct Injection ◽  
Engine Performance ◽  
Specific Fuel Consumption ◽  
Gasoline Direct Injection ◽  
Fire Temperature ◽  
Air Temperatures ◽  
Performance And Emissions ◽  
And Performance

In the present work, the direct-injection petrol engine (GDI) combustion, emissions and performance at different engine speeds (1500, 2000, 2500 and 3000 rpm) with a constant throttle position have been studied. The fuel considered in this work is liquid petroleum gas (LPG) and gasoline. The software adopted in all simulations by the AVL BOOST 2016. A Hyundai 2.0 liter, 16 valves and 4 cylinders engine with a compression ratio 17.5:1 is used. The effect of several inlet air temperatures (0, 10, 20, 30, 40 and 50 oC) on the engine performance, combustion and emissions are also studied. The results show that the increase in the inlet air temperature leading to increase the peak fire temperature, brake specific fuel consumption (BSFC) and nitrogen oxide (NOx). However, this process results in a reduction in the peak fire pressure, combustion period (duration), brake power and brake torque. The maximum fire temperature and maximum specific fuel consumption can be achieved when the engine speed is 3000 rpm and the inlet air temperature is 50 ºC.

Variable Geometry, Lean, Premixed, Prevaporized Fuel Combustor Conceptual Design Study

1980 ◽  
Vol 102 (4) ◽  
pp. 896-902 ◽  
Author(s):  
A. J. Fiorentino ◽  
W. Greene ◽  
J. C. Kim ◽  
E. J. Mularz
Keyword(s):  
Conceptual Design ◽  
Combustion Efficiency ◽  
Operating Conditions ◽  
Nox Emissions ◽  
Variable Geometry ◽  
Design Study ◽  
Flow Modulation ◽  
Lean Premixed ◽  
Unburned Hydrocarbons ◽  
And Performance

Four lean premixed prevaporized (LPP) combustor concepts have been identified which utilize variable geometry and/or other flow modulation techniques to control the equivalence ratio of the initial burning zone. Lean equivalence ratios are maintained at high power engine operating conditions for low NOx emissions, while near stoichiometric conditions are maintained at low power for good combustion efficiency and low emissions of carbon monoxide and unburned hydrocarbons. The primary goal of this program was to obtain a low level of NOx emissions (≤3 g/kg fuel) at stratospheric cruise conditions; additional goals are to achieve the currently proposed 1984 EPA emission standards over the landing/take off cycle and performance and operational requirements typical of advanced aircraft engines. Based on analytical projections made during this conceptual design study, two of the concepts offer the potential of achieving the emission goals. However, the projected operational characteristics and reliability of these concepts to perform satisfactorily over an entire flight envelope would require extensive experimental substantiation before an engine application can be considered.

scholarly journals Full Annular Rig Development of the FT8 Gas Turbine Combustor

1990 ◽  
Author(s):  
T. G. Fox ◽  
B. C. Schlein
Keyword(s):  
Gas Turbine ◽  
Liquid Fuel ◽  
Water Injection ◽  
Gas Turbine Combustor ◽  
Exit Temperature ◽  
Reduce Emissions ◽  
Engine Testing ◽  
And Performance ◽  
Industrial Gas Turbine ◽  
Emissions And Performance

The results of developmental testing in a high pressure, full annular combustion section af the FT8 industrial gas turbine are presented. Base power conditions were simulated at approximately 60% of burner pressure. All aspects of combustion performance with liquid fuel were investigated, including starting, blowout, exit temperature signature, emissions, smoke and liner wall temperature. Configurational changes were made to improve liner cooling, reduce emissions, adjust pressure loss and modify exit temperature profile. The effects of water injection on emissions and performance were evaluated in the final test run. Satisfactory performance in all areas was demonstrated with further refinements to be carried out during developmental engine testing.

Full Annular Rig Development of the FT8 Gas Turbine Combustor

1992 ◽  
Vol 114 (1) ◽  
pp. 27-32 ◽  
Author(s):  
T. G. Fox ◽  
B. C. Schlein
Keyword(s):  
Gas Turbine ◽  
Liquid Fuel ◽  
Water Injection ◽  
Gas Turbine Combustor ◽  
Exit Temperature ◽  
Reduce Emissions ◽  
Engine Testing ◽  
And Performance ◽  
Industrial Gas Turbine ◽  
Emissions And Performance

The results of developmental testing in a high-pressure, full annular combustion section of the FT8 industrial gas turbine are presented. Base power conditions were simulated at approximately 60 percent of burner pressure. All aspects of combustion performance with liquid fuel were investigated, including starting, blowout, exit temperature signature, emissions, smoke, and liner wall temperature. Configurational change were made to improve liner cooling, reduce emissions, adjust pressure loss, and modify exit temperature profile. The effects of water injection on emissions and performance were evaluated in the final test run. Satisfactory performance in all areas was demonstrated with further refinements to be carried out during developmental engine testing.

On the dynamics of distribution of the American White Butterfly, Hyphantria cunea Drury, 1973 (Lepidoptera, Arctiidae), in Ukraine regarding the annual minimal air temperatures

2018 ◽  
Vol 14 (1) ◽  
pp. 44-57
Author(s):  
S. N. Shumov
Keyword(s):  
Air Temperature ◽  
Annual Reports ◽  
Complete Elimination ◽  
Hyphantria Cunea ◽  
White American ◽  
Gis Technologies ◽  
Data Analyses ◽  
Air Temperatures ◽  
Negative Temperatures

The spatial analysis of distribution and quantity of Hyphantria cunea Drury, 1973 across Ukraine since 1952 till 2016 regarding the values of annual absolute temperatures of ground air is performed using the Gis-technologies. The long-term pest dissemination data (Annual reports…, 1951–1985; Surveys of the distribution of quarantine pests ..., 1986–2017) and meteorological information (Meteorological Yearbooks of air temperature the surface layer of the atmosphere in Ukraine for the period 1951-2016; Branch State of the Hydrometeorological Service at the Central Geophysical Observatory of the Ministry for Emergencies) were used in the present research. The values of boundary negative temperatures of winter diapause of Hyphantria cunea, that unable the development of species’ subsequent generation, are received. Data analyses suggests almost complete elimination of winter diapausing individuals of White American Butterfly (especially pupae) under the air temperature of −32°С. Because of arising questions on the time of action of absolute minimal air temperatures, it is necessary to ascertain the boundary negative temperatures of winter diapause for White American Butterfly. It is also necessary to perform the more detailed research of a corresponding biological material with application to the freezing technics, giving temperature up to −50°С, with the subsequent analysis of the received results by the punched-analysis.

Study on Common Ground Testing Platform Technology for Telemetry Core Equipment

2012 ◽  
Vol 220-223 ◽  
pp. 1472-1475
Author(s):  
Qiu Lin Tan ◽  
Xiang Dong Pei ◽  
Si Min Zhu ◽  
Ji Jun Xiong
Keyword(s):  
Data Exchange ◽  
Common Ground ◽  
Digital Signal ◽  
Test System ◽  
Automatic Test System ◽  
Module Design ◽  
The Status ◽  
Output Module ◽  
And Performance ◽  
Hardware Circuit

On the basis of automatic test system of the status in domestic and foreign, by analysis of the various functions and performance of the integrated test system, a design of the integrated test system is proposed, FPGA as the core logic controller of the hardware circuit. The system of the hardware design include: digital signal source output modules, analog output module and PCM codec module. Design of hardware circuit are mainly described. In addition, a detailed analysis of some key technologies in the design process was given. Overall, its data exchange with host computer is through the PCI card, data link and bandwidth can be expanded in accordance with the actual needs. The entire system designed in the modular principle, which has a strong scalability.

scholarly journals The Light Microscopy Module Design and Performance Demonstrations

2003 ◽  
Author(s):  
Susan Motil ◽  
John Snead ◽  
DeVon Griffin ◽  
Edward Hovenac
Keyword(s):  
Light Microscopy ◽  
Module Design ◽  
And Performance
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