scholarly journals Fuel Character Effects on J79 and F101 Engine Combustor Emissions

1980 ◽  
Author(s):  
C. C. Gleason ◽  
J. A. Martone
Keyword(s):  
Air Force ◽  
Hydrogen Content ◽  
Pollutant Emissions ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Oxides Of Nitrogen ◽  
Fuel Property ◽  
Fuel Atomization ◽  
Us Air Force ◽  
Point Data

Results of a program to determine the effects of fuel properties on the pollutant emissions of two US Air Force aircraft gas turbine engines are presented. Thirteen test fuels, including baseline JP-4 and JP-8, were evaluated in a cannular (J79) and a full annular (F101) combustor. The principal fuel variables were hydrogen content, aromatic structure, volatility, and distillation end point. Data analysis shows that fuel hydrogen content is a key fuel property, particularly with respect to high power emissions (oxides of nitrogen and smoke), and that low power emissions (carbon monoxide and hydrocarbons) are more dependent on fuel atomization and evaporation characteristics.

scholarly journals The Evaluation of Fuel Property Effects on Air Force Gas Turbine Engines Program Genesis

1981 ◽  
Author(s):  
T. A. Jackson
Keyword(s):  
Gas Turbine ◽  
Air Force ◽  
Fuel Properties ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Test Results ◽  
Fuel Property ◽  
Fuel Nozzle ◽  
Fuel Effects ◽  
System Selection

The Air Force has conducted a series of investigations to quantify the effects of certain fuel properties on the operability and durability of its aircraft gas turbine engines. Initially these efforts were conducted on a small number of engines intended to be representative of the majority of gas turbine engines in the Air Force inventory. The testing was conducted exclusively in rigs representing the combustor and fuel nozzle components of these engines of interest. Test fuels for these programs were primarily blends of hydrocarbons. These test fuels exhibited significant variations in several major fuel properties. Based on results of these evaluations a second generation of test activity in fuel effects area was formulated. Engine system selection was broadened to include more considerations. Test fuels were reduced in number and priorities for modification of certain fuel properties were adjusted. This paper presents dominant test results of early fuel effects programs and supplemental background which dictated the structure of the second, more comprehensive program.

The Effects of Ambient Conditions on Gas Turbine Emissions—Generalized Correction Factors

1978 ◽  
Vol 100 (4) ◽  
pp. 640-646 ◽  
Author(s):  
P. Donovan ◽  
T. Cackette
Keyword(s):  
Gas Turbine ◽  
Pressure Ratio ◽  
Turbine Engines ◽  
Inlet Temperature ◽  
Gas Turbine Engines ◽  
Correction Factors ◽  
Oxides Of Nitrogen ◽  
Ambient Conditions ◽  
Nitrogen Emission ◽  
Wide Range

A set of factors which reduces the variability due to ambient conditions of the hydrocarbon, carbon monoxide, and oxides of nitrogen emission indices has been developed. These factors can be used to correct an emission index to reference day ambient conditions. The correction factors, which vary with engine rated pressure ratio for NOx and idle pressure ratio for HC and CO, can be applied to a wide range of current technology gas turbine engines. The factors are a function of only the combustor inlet temperature and ambient humidity.

scholarly journals Development of 300 kW Class Ceramic Gas Turbine (CGT302)

1995 ◽  
Author(s):  
Kozi Nishio ◽  
Junzo Fujioka ◽  
Tetsuo Tatsumi ◽  
Isashi Takehara
Keyword(s):  
Gas Turbine ◽  
Development Program ◽  
Pollutant Emissions ◽  
Turbine Engines ◽  
Inlet Temperature ◽  
Gas Turbine Engines ◽  
Turbine Inlet Temperature ◽  
Iso Standard ◽  
Current State ◽  
Ceramic Components

With the aim of achieving higher efficiency, lower pollutant emissions, and multi-fuel capability for small to medium-sized gas turbine engines for use in co-generation systems, a ceramic gas turbine (CGT) research and development program is being promoted by the Japanese Ministry of International Trade and Industry (MITI) as a part of its “New Sunshine Project”. Kawasaki Heavy Industries (KHI) is participating in this program and developing a regenerative two-shaft CGT (CGT302). In 1993, KHI conducted the first test run of an engine with full ceramic components. At present, the CGT302 achieves 28.8% thermal efficiency at a turbine inlet temperature (TIT) of 1117°C under ISO standard conditions and an actual TIT of 1250°C has been confirmed at the rated speed of the basic CGT. This paper consists of the current state of development of the CGT302 and how ceramic components are applied.

scholarly journals Application of a Thermal-Hydraulic Management Model to Gas Turbine Combustors and Fuel Systems

1999 ◽  
Author(s):  
M. A. Mawid ◽  
C. A. Arana ◽  
B. Sekar
Keyword(s):  
Gas Turbine ◽  
Air Force ◽  
Turbine Engines ◽  
Analysis Tool ◽  
Flow Control Valve ◽  
Engine Fuel ◽  
Gas Turbine Engines ◽  
Fuel System ◽  
Analysis And Design ◽  
Fuel Flow

An advanced thermal management analysis tool, named Advanced Thermal Hydraulic Energy Network Analyzer (ATHENA), has been used to simulate a fuel system for gas turbine engines. The ATHENA tool was modified to account for JP-8/dodecane fuel properties. The JP-8/dodecane fuel thermodynamic properties were obtained from the SUPERTRAP property program. A series of tests of a fuel system simulator located at the Air Force Research Laboratory (AFRL)/Wright Patterson Air Force Base were conducted to characterize the steady state and dynamic behavior of the fuel system. Temperature, pressures and fuel flows for various fuel pump speeds, pressure rise and flow control valve stem positions (orifice areas), heat loads and engine fuel flows were measured. The predicted results were compared to the measured data and found to be in excellent agreement. This demonstrates the capability of the ATHENA tool to reproduce the experimental data and, consequently, its validity as an analysis tool that can be used to carry out analysis and design of fuel systems for advanced gas turbine engines. However, some key components in the fuel system simulator such as control components, which regulate the engine fuel flow based on predetermined parameters such as fan speed, compressor inlet and exit pressures and temperatures, combustor pressure, turbine temperature and power demand, were not simulated in the present investigation due to their complex interactions with other components functions. Efforts are currently underway to simulate the operation of the fuel system components with control as the engine fuel flow and power demands are varied.

scholarly journals Characteristic Time Correlations of Pollutant Emissions From an Annular Gas Turbine Combustor

1979 ◽  
Author(s):  
A. M. Mellor ◽  
R. M. Washam
Keyword(s):  
Gas Turbine ◽  
Characteristic Time ◽  
Pollutant Emissions ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Gas Turbine Combustor ◽  
Time Model ◽  
Gaseous Pollutant ◽  
Modeling Approach ◽  
Time Correlations

The continuing development of a characteristic time model for gaseous pollutant emissions from conventional gas turbine engines is described. The now engine studied here is the Pratt and Whitney JT9D, and it is shown that universal correlations can be obtained by comparison with previous results. Current limitations of the modeling approach are detailed.

Deposits From Heated Gas Turbine Fuels

1976 ◽  
Author(s):  
E. J. Szetela
Keyword(s):  
Gas Turbine ◽  
Air Force ◽  
Gas Turbines ◽  
Turbine Engines ◽  
Naval Research ◽  
Gas Turbine Engines ◽  
Chemical Mechanisms ◽  
Fuel Vaporization ◽  
Physical And Chemical ◽  
Development Center

Deposits from gas turbine fuels are a major concern when prevaporized-premixed combustor concepts are considered for gas turbine engines. Even in conventional gas turbines, deposits are occasionally found in fuel nozzles after a long period of operation. A search was made for information regarding deposits from heated gas turbine fuels using open literature data and data generated within United Technologies Corporation. Summaries of both the data obtained from this survey and the physical and chemical mechanisms leading to the formation of fuel deposits are presented. Data obtained by Pratt and Whitney Aircraft at the Florida Research and Development Center indicate that deposits were suppressed while the fuel was vaporized by mixing with air at velocities of 6 to 13 fps (15 to 33 cm/sec) and pressures of 50 to 200 psia (3.4 to 14 atm). Data obtained at United Technologies Research Center showed that deposits can also be prevented by intermittent use of heated air. Data obtained at EXXON and at the Naval Research Laboratory show that although deposits increase with temperature, a peak is found at about 700 F (682 K). Fuel vaporization was shown to increase the deposit levels in experiments at the Air Force Aero Propulsion Laboratory.

Modeling of Particle Wall Interaction and Film Transport Using Eulerian Wall Film Model

2014 ◽  
Author(s):  
Rahul Ingle ◽  
Ravi Yadav ◽  
Hemant Punekar ◽  
Jing Cao
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Turbine Blades ◽  
Continuous Phase ◽  
Pollutant Emissions ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Secondary Atomization ◽  
Wall Film ◽  
Wall Interaction

The growing awareness of pollutant emissions from gas turbines has made it very important to study fuel atomization system, the spray wall interaction and hydrodynamic of film formed on engine walls. A precise fuel spray spatial distribution and efficient fuel air mixing plays important role in improving combustion performance. Cross-flow injection and film atomization technique has been studied extensively for gas turbine engines to achieve efficient combustion. Air blast atomizer is one of these kind of systems used in gas turbine engines which involves shear driven prefilmer secondary atomization. In addition to gas turbine combustor shear driven liquid wall film can be seen in IC engines, rocket nozzles, heat exchangers and also on steam turbine blades. In our work we have used Eulerian Wall Film (EWF) [1] model to simulate the experiment performed by Arienti et al. [2]. In the Arienti’s experiment liquid jet is injected from a nozzle from the top of the chamber. Droplets shed from the jet surface due to primary and later secondary atomization in the presence of high shearing cross flowing air. Further liquid fuel particles hit the wall to form film, film moves subjected to shear from the gas phase. Liquid film can reatomizes due to subgrid processes like stripping, splashing and film breakup. In current study we have validated Arienti et al. [2] experimental data by modeling complex & coupled physics of spray, film and continuous phase and by accounting complex subgrid processes.

Lean Blowout Research in a Generic Gas Turbine Combustor With High Optical Access

1993 ◽  
Author(s):  
G. J. Sturgess ◽  
D. Shouse
Keyword(s):  
Experimental Data ◽  
Gas Turbine ◽  
Air Force ◽  
Operating Conditions ◽  
Test Facility ◽  
Turbine Engines ◽  
Flame Stability ◽  
Gas Turbine Engines ◽  
Gas Turbine Combustor ◽  
Lean Blowout

The U.S. Air Force is conducting a comprehensive research program aimed at improving the design and analysis capabilities for flame stability and lean blowout in the combustors of aircraft gas turbine engines. As part of this program, a simplified version of a generic gas turbine combustor is used. The intent is to provide an experimental data base against which lean blowout modeling might be evaluated and calibrated. The design features of the combustor and its instrumentation are highlighted, and the test facility is described. Lean blowout results for gaseous propane fuel are presented over a range of operating conditions at three different dome flow splits. Comparison of results with those of a simplified research combustor is also made. Lean blowout behavior is complex, so that simple phenomenological correlations of experimental data will not be general enough for use as design tools.

Directions in High Temperature Intermetallics Research

1988 ◽  
Vol 133 ◽  
Author(s):  
Dennis M. Dimiduk ◽  
Daniel B. Miracle
Keyword(s):  
High Temperature ◽  
Air Force ◽  
Evolutionary Process ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Paper Briefly ◽  
Research Directions ◽  
Intermetallic Materials ◽  
Turbine Performance ◽  
Structural Intermetallic

ABSTRACTStructural intermetallic materials have undergone an evolutionary process whereby some of the materials could provide major payoffs in gas turbine engines. This maturation of select intermetallic systems has provided significant hope for making still greater advances in turbine performance through further developments in other intermetallic materials. The same maturation process has highlighted specific limitations and requirements which are key to the utilization of intermetallic systems. This paper briefly reviews some critical ground rules for high temperature intermetallics development and identifies research directions being pursued by the Air Force for advancing intermetallic materials.

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