Fuel Systems for Gas Turbine Engines

1955 ◽  
Vol 59 (539) ◽  
pp. 727-737 ◽  
Author(s):  
O. N. Lawrence
Keyword(s):  
Gas Turbine ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Fuel System ◽  
Fuel Flow ◽  
Design Office ◽  
System Engineer ◽  
Made In

Seven years ago a paper on this same subject was read before the Main Society. This has been used as a basis from which to start.It will be seen that great strides have been made in performance, and the projects in the Design Office and on the drawing boards particularly, would even satisfy parliamentary critics. In Derby, however, where jet lift was conceived, such things are well known. From the fuel system standpoint in general the changes in requirements have been routine, merely much greater fuel demands, greater altitudes and air speeds and hence, a greater range of fuel flow, and it is this which gives the fuel system engineer his greatest worries. Beyond this there is always the need for smaller and lighter units in fancy shapes.

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.

Acceleration Performance Analysis of a Gas Turbine Destroyer Escort

1971 ◽  
Vol 93 (1) ◽  
pp. 49-55 ◽  
Author(s):  
A. Bodnaruk ◽  
C. J. Rubis
Keyword(s):  
Gas Turbine ◽  
Reduction Gear ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Flow Rates ◽  
Operating Modes ◽  
Single Screw ◽  
Fuel Flow ◽  
Quantitative Results ◽  
Thrust And Torque

The dynamic acceleration performance of a single screw destroyer escort driven by two FT4A-2 gas turbine engines through a reversing reduction gear was analyzed. The analysis was carried out on a digital computer using a new method of a second modified advance coefficient to represent propeller thrust and torque coefficients. Quantitative results for all the major ship and propulsion plant parameters are given for the ship in a calm sea with no turning motions during fuel scheduled acceleration in the base and base-plus-boost operating modes. Control of fuel flow rates using fuel ramps with varying time bases was found to be effective in limiting engine overtorque conditions during acceleration. Other conclusions on transient thrust, acceleration time, and head reach are also presented.

Integration of Control and Fuel System Components Today and Tomorrow

1969 ◽  
Author(s):  
L. J. Moulton
Keyword(s):  
Control Systems ◽  
Gas Turbine ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Fuel System ◽  
New Techniques ◽  
Additional Weight ◽  
Time Control ◽  
System Components ◽  
Improved Performance

New gas turbine engines, because of their requirements for improved performance at lower weights, are placing additional requirements on the control and fuel system. At the same time control and fuel system must weigh less. Integration of certain control and fuel system components is one approach which has allowed some of these seemingly conflicting requirements to be met. While future control systems may be able to achieve some additional weight savings by additional integration, further use of new techniques particularly those in electronic and pneumatic computational components seem areas to be explored if step reductions in control weight and volume are to be attained.

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

Potential Application of Composite Materials to Future Gas Turbine Engines

1988 ◽  
Author(s):  
James C. Birdsall ◽  
William J. Davies ◽  
Richard Dixon ◽  
Matthew J. Ivary ◽  
Gary A. Wigell
Keyword(s):  
Composite Materials ◽  
Gas Turbine ◽  
Potential Application ◽  
Turbine Engines ◽  
Gas Turbine Engines

Method of tribodiagnostics of d-30KU engines/KP with the use of a microwave plasma complex: results of metrological examination and analysis of the accuracy

2020 ◽  
pp. 22-29
Author(s):  
A. Bogoyavlenskiy ◽  
A. Bokov
Keyword(s):  
Gas Turbine ◽  
Microwave Plasma ◽  
Technical Condition ◽  
The State ◽  
Turbine Engines ◽  
Metrological Examination ◽  
Gas Turbine Engines ◽  
High Frequency Plasma ◽  
Frequency Plasma ◽  
Primary Standards

The article contains the results of the metrological examination and research of the accuracy indicators of a method for diagnosing aircraft gas turbine engines of the D30KU/KP family using an ultra-high-frequency plasma complex. The results of metrological examination of a complete set of regulatory documents related to the diagnostic methodology, and an analysis of the state of metrological support are provided as well. During the metrological examination, the traceability of a measuring instrument (diagnostics) – an ultrahigh-frequency plasma complex – is evaluated based on the scintillation analyzer SAM-DT-01–2. To achieve that, local verification schemes from the state primary standards of the corresponding types of measurements were built. The implementation of measures to eliminate inconsistencies identified during metrological examination allows to reduce to an acceptable level the metrological risks of adverse situations when carrying out aviation activities in industry and air transportation. In addition, the probability of occurrence of errors of the first and second kind in the technological processes of tribodiagnostics of aviation gas turbine engines is reduced when implementing a method that has passed metrological examination in real practice. At the same time, the error in determining ratings and wear indicators provides acceptable accuracy indicators and sufficient reliability in assessing the technical condition of friction units of the D-30KP/KP2/KU/KU-154 aircraft engines.

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