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.

High density fuel effects on gas turbine engines

1987 ◽  
Author(s):  
V. OECHSLE ◽  
P. ROSS ◽  
H. MONGIA
Keyword(s):  
Gas Turbine ◽  
High Density ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Fuel Effects

U.S. Navy Development of Air Assist Fuel Nozzle System for the 501K Series Gas Turbine Engines

2002 ◽  
Author(s):  
Matthew G. Hoffman ◽  
Richard J. DeCorso ◽  
Dennis M. Russom
Keyword(s):  
Gas Turbine ◽  
Failure Modes ◽  
Development Program ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Engine Operation ◽  
Air Blast ◽  
Blast Design ◽  
Fuel Nozzle ◽  
The U.S

The U.S. Navy has experienced problems with liquid fuel nozzles used on the Rolls Royce (formerly Allison) 501K series marine gas turbine engines. The 501K engines used by the U.S. Navy power Ship Service Gas Turbine Generators (SSGTGs) on a number of destroyer and cruiser class ships. Over roughly the last 25 years, 3 different nozzle designs have been employed, the latest and current nozzle being a piloted air blast design. The primary failure modes of these designs were internal fuel passage coking and external carbon deposits. The current piloted air blast design has a hard time replacement requirement of 1500 hours. This life is considered unacceptable. To improve fuel nozzle life, the Navy and Turbine Fuel Technologies (formerly Delavan) teamed in a fast track program to develop a new fuel nozzle with a target life of 5000 hours and 500 starts. As a result, an air assist/air blast nozzle was developed and delivered in approximately 6 months. In addition to the nozzle itself, a system was developed to provide assist air to the fuel nozzles to help atomize the fuel for better ignition. Nozzle sets and air assist systems have been delivered and tested at the NSWC Philadelphia LBES (Land Based Engineering Site). In addition, nozzle sets have been installed aboard operating ships for in-service evaluations. During the Phase one evaluation (July 2000 to June 2001) aboard USS Porter (DDG 78) a set of nozzles accumulated over 3500 hours of trouble free operation, indicating the target of 5000 hours is achievable. As of this writing these nozzles have in excess of 5700 hours. The improvements in nozzle life provided by the new fuel nozzle design will result in cost savings through out the life cycle of the GTGS. In fact, the evaluation nozzles are already improving engine operation and reliability even before the nozzles’ official fleet introduction. This paper describes the fuel nozzle and air assist system development program and results of OEM, LBES and fleet testing.

On-Line Detergent Washing: Reducing the Environmental Effects on the LCAC Gas Turbine Engines

1992 ◽  
Author(s):  
Jeffrey S. Patterson ◽  
Soren K. Spring
Keyword(s):  
Gas Turbine ◽  
Systems Engineering ◽  
Present Method ◽  
Engine Performance ◽  
Turbine Engines ◽  
Harsh Environment ◽  
Gas Turbine Engines ◽  
Test Results ◽  
On Line ◽  
Air Cushion

The Landing Craft Air Cushion (LCAC) gas turbine engines operate in an extremely harsh environment and are exposed to excessive amounts of foreign contaminants. The present method of crank washing is effective when properly performed, but is labor intensive and increases craft downtime. Naval Ship Systems Engineering Station (NAVSSES) designed and installed a prototype on-line detergent wash system which reduced maintenance and craft downtime. Initial test results indicated that the system reduced engine performance degradation and corrosion.

Internally Generated Noise From Gas Turbine Engines. Measurement and Prediction

1967 ◽  
Vol 89 (2) ◽  
pp. 177-185 ◽  
Author(s):  
M. J. T. Smith ◽  
M. E. House
Keyword(s):  
Gas Turbine ◽  
Full Scale ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Test Results ◽  
Radiation Patterns ◽  
Noise Sources ◽  
Prediction Technique ◽  
Noise Measurements ◽  
Engine Compressor

The noise sources from gas turbine engines are defined and their radiation patterns identified from test results. Examination of single-stage and full-scale engine compressor noise measurements leads to a prediction technique being evolved for inlet and efflux levels.

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.

scholarly journals Why an Engine Air Particle Separator (EAPS)?

1990 ◽  
Author(s):  
Joe Thomas Potts
Keyword(s):  
Gas Turbine ◽  
Volcanic Ash ◽  
Vortex Generator ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Test Results ◽  
Turbine Engine ◽  
Industrial Pollutants ◽  
Air Intake ◽  
Particle Separator

The purpose of this technical paper is to describe how an Engine Air Particle Separator (EAPS) removes contaminant particles before they enter the gas turbine engine. Gas turbine engines perform poorly in air containing sand, volcanic ash, industrial pollutants, etc. Typical dirt related gas turbine malfunctions include: • Erosion of the engine and air cycle machinery rotating components. • Clogging and fouling of turbine section. • Wear of oil wetted components caused by contaminated lubricants. Contaminated air entering an EAPS is sent through a swirling motion induced by the vortex generator. This swirling motion causes the heavier dirt particles and water droplets to be thrown radially outward by centrifugal force so that they may be scavenged from the engine air intake. This report will provide test results of helicopters with and without EAPS and describes the steps necessary to design an EAPS for various air vehicles and engines.

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.

Sign in / Sign up

Export Citation Format

Share Document