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.

scholarly journals Spa “Mashproekt” Reversible Power Turbines

1994 ◽  
Author(s):  
V. I. Romanov ◽  
O. G. Zhiritsky ◽  
V. E. Belyaev ◽  
V. V. Lupandin
Keyword(s):  
Gas Turbine ◽  
Production Association ◽  
Reduction Gear ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Design Features ◽  
Specific Design ◽  
Design Simplicity ◽  
Former Ussr

The gas turbine engines incorporating reversible power turbines have been designed and developed by the MASHPROEKT Scientific and Production Association (SPA). They are widely used for powering the former USSR (Russia) Navy ships, as well as the CAPITAN SMIRNOV Ro-Ro type cargo vessels. The GT 3000, GT 8000, GT 15000 and D59 gas turbine engines comprise reversible power turbines. Compared with other marine reversible devices (reversing reduction gear, controllable pitch propeller), the reversible gas turbine has advantages in maneuvrability, reliability and design simplicity. This paper presents specific design features of the SPA MASHPROEKT reversible power turbines.

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.

High Response Valve for Active Combustion Control

2001 ◽  
Author(s):  
Dong N. Wu ◽  
Joseph W. Michalski ◽  
Link C. Jaw ◽  
Kenneth Semega
Keyword(s):  
Gas Turbine ◽  
Piezoelectric Actuator ◽  
High Response ◽  
Turbine Engines ◽  
Bench Test ◽  
Gas Turbine Engines ◽  
Combustion Control ◽  
Flow Rates ◽  
Active Combustion Control ◽  
Modulation Control

This paper describes the development of a prototype high response fuel valve using piezoelectric actuator for fuel modulation control in gas turbine engines. In flow bench test, this prototype valve demonstrated 5∼11% peak-to-peak modulation strength at flow rates up to approximately 1500 pph and frequencies up to 500 Hz.

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 Identification of a mathematical model for a single-shaft power-generating GTE

Energetika ◽  
2021 ◽  
Vol 67 (1) ◽  
Author(s):  
Anatoly Tarelin ◽  
Alexander Lyutikov ◽  
Iryna Annopolska
Keyword(s):  
Mathematical Model ◽  
Mathematical Models ◽  
Gas Turbine ◽  
Parametric Identification ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Variable Parameters ◽  
Operating Modes ◽  
Model Linearization ◽  
The Mathematical Model

The design and development processes of gas turbine engines rely on the usage of mathematical models representing the physics of engine functioning processes. One way of increasing the validity of a mathematical model is its identification based on engine test results. The identification of mathematical models of modern power-generating gas turbine engines (GTEs) presents a demanding and time-consuming task due to the necessity to identify the main controlled engine parameters determined in the course of experimental studies depending on a large number of the parameters that are not controlled during the experiment. In this regard the actual direction of reducing the labour intensity of the process of mathematical model identification is using identification program complexes. The object of the study was to solve the problem of structural-parametrical identification of the power-generating GTE functioning model detailing the turbine flow path calculations to the level of blade rows in order to obtain the GTE mathematical model that describes the characteristics of a real engine with given accuracy. To achieve the objective, the following problems were solved: variable parameters, controlled parameters and characteristics, ranges of their variations were selected from the total number of the mathematical model input data, the objective functions were defined; the task of the parametric identification according to the results of bench tests through GTE operating modes was performed; analytical approximating dependences for correcting coefficients (variable parameters) were obtained; structural-parametric identification of the mathematical model was performed. The novelty of the obtained results is the identification of the mathematical model of the nonlinear component GTE of the second level performed without model linearization (without its level lowering) by using the Optimum software packages. The methodological approach for the parametric identification of the mathematical model is proposed. This approach allows reducing the number of variable parameters under the modes lower that the maximum. It shows that the identified model allows obtaining the prediction results of the GTE parameters and characteristics through operating modes with a deviation of no more than 1.4% from the experimental data and, therefore, it will allow reduction of terms and an increase in the quality of power unit development.

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
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