Fuel Property Effects on Air Force Gas Turbine Engines-Program Genesis

1982 ◽  
Vol 6 (6) ◽  
pp. 376-383 ◽  
Author(s):  
T.A. Jackson
Keyword(s):  
Gas Turbine ◽  
Air Force ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Fuel Property

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.

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 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.

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.

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.

scholarly journals Automated Diagnostic System for Engine Maintenance

1983 ◽  
Author(s):  
Frank Fanuele ◽  
Richard A. Rio
Keyword(s):  
Gas Turbine ◽  
Air Force ◽  
Gas Turbines ◽  
Diagnostic System ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Data Set ◽  
Jet Engine ◽  
Vibration Data ◽  
Engine Maintenance

The rapidly increasing costs of maintenance, the demand for increased equipment utilization, fuel costs and the difficulty of correctly diagnosing internal mechanical problems in operating gas turbine engines has stressed the requirement for more effective monitoring and diagnostic equipment. Such equipment must be capable of performing three functions: 1. Acquiring condition data from operating gas turbines, 2. Analyzing the acquired data, and 3. Associating the cause and effect relationship to an incipient malfunction. This paper describes the MTI Automated Vibration Diagnostic System (AVID) developed for the U. S. Air Force jet engine overhaul centers. The AVID concept is to automate troubleshooting procedures for fully assembled gas turbine engines. The System extracts high-frequency vibration data from existing, standard instrumentation to provide input to a specialized Symptom/Fault Matrix. This Symptom/Fault Matrix is configured to analyze the incoming data and assign a particular malfunction (or malfunctions) to a specified data set. This diagnosis is then printed out to provide maintenance personnel with exact knowledge of what the problem is and how to correct it. This System, plus the growing awareness on the part of personnel of the capabilities of such automated equipment, will enable the Air Force to significantly reduce expenses at their jet engine overhaul facilities.

Competitive Acquisition: What Makes Sense for Engines?

1988 ◽  
Author(s):  
Michael S. Coalson
Keyword(s):  
Gas Turbine ◽  
Air Force ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Weapon System ◽  
Competitive Position ◽  
Initial Cost ◽  
Acquisition Strategies

Acquisition of aeronautical gas turbine engines is a very critical and very expensive aspect of weapon system procurement. The Air Force uses various acquisition strategies in developing and procuring new engines which have the intent of reducing cost in both buying and operating engines. One of those strategies is the fostering of competition. The topic of this paper is to review various opportunities for fostering competition and to describe areas, other than the obvious one of initial cost, where a responsive contractor can enhance his competitive position. We will consider only opportunities for competition at the prime contractor level; vendor and spares competition are left for other papers.

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

1997 ◽  
Vol 119 (1) ◽  
pp. 108-118 ◽  
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.

Gas Screen in Components of Gas Turbine Engines

1997 ◽  
Vol 28 (7-8) ◽  
pp. 536-542
Author(s):  
A. A. Khalatov ◽  
I. S. Varganov
Keyword(s):  
Gas Turbine ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Gas Screen
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