scholarly journals Gas Turbine Engine Behavioral Modeling

2015 ◽  
Vol 137 (12) ◽  
Author(s):  
Richard T. Meyer ◽  
Raymond A. DeCarlo ◽  
Steve Pekarek ◽  
Chris Doktorcik
Keyword(s):  
Gas Turbine ◽  
Energy Flow ◽  
Power Flow ◽  
Time Derivative ◽  
Behavioral Model ◽  
Electric Utility ◽  
Gas Turbine Engine ◽  
Gas Generator ◽  
Turbine Engine ◽  
Mathematical Expressions

This paper develops and validates a power flow behavioral model of a gas turbine engine (GTE) composed of a gas generator and free power turbine. The behavioral model is suitable for supervisory level (optimal) controller development of the engine itself or of electrical power systems containing gas-turbine-generator pairs as might be found in a naval ship or terrestrial electric utility plant. First principles engine models do not lend themselves to the supervisory level control development because of their high granularity. For the behavioral model, “simple” mathematical expressions that describe the engine's internal power flows are derived from an understanding of the engine's internal thermodynamic and mechanical interactions. These simple mathematical expressions arise from the balance of energy flow across engine components, power flow being the time derivative of energy flow. The parameter fit of the model to a specific engine such as the GE LM2500 detailed in this work utilizes constants and empirical fits of power conversion efficiencies obtained using data collected from a high-fidelity engine simulator such as the Gas Turbine Simulation Program (GSP). Transient response tests show that the two-norm normalized error between the detailed simulator model and behavioral model outputs to be 2.7% or less for a GE LM2500.

scholarly journals A Parametric Starting Study of an Axial-Centrifugal Gas Turbine Engine Using a One-Dimensional Dynamic Engine Model and Comparisons to Experimental Results: Part 1 — Model Development and Facility Description

1998 ◽  
Author(s):  
A. Karl Owen ◽  
Anne Daugherty ◽  
Doug Garrard ◽  
Howard C. Reynolds ◽  
Richard D. Wright
Keyword(s):  
Gas Turbine ◽  
Initial Conditions ◽  
Model Development ◽  
Ground Level ◽  
Gas Turbine Engine ◽  
Calibration Data ◽  
Gas Generator ◽  
Turbine Engine ◽  
One Dimensional ◽  
Engine Model

A generic one-dimensional gas turbine engine model, developed at the Arnold Engineering Development Center, has been configured to represent the gas generator of a General Electric axial-centrifugal gas turbine engine in the six kg/sec airflow class. The model was calibrated against experimental test results for a variety of initial conditions to insure that the model accurately represented the engine over the range of test conditions of interest. These conditions included both assisted (with a starter motor) and unassisted (altitude windmill) starts. The model was then exercised to study a variety of engine configuration modifications designed to improve its starting characteristics and thus quantify potential starting improvements for the next generation of gas turbine engines. This paper discusses the model development and describes the test facilities used to obtain the calibration data. The test matrix for the ground level testing is also presented. A companion paper presents the model calibration results and the results of the trade-off study.

Experimental Investigation of an Inert Gas Generator for Fire Suppressing

2001 ◽  
Author(s):  
SooYong Kim ◽  
A. Slitenko
Keyword(s):  
Experimental Investigation ◽  
Gas Turbine ◽  
Mass Flow Rate ◽  
Oxygen Content ◽  
Flow Rate ◽  
Gas Turbine Engine ◽  
Inert Gas ◽  
Gas Generator ◽  
Turbine Engine ◽  
Exit Nozzle

Present study deals with experimental and theoretical performance analysis of an inert gas generator(IGG) which can be used as an effective mean to suppress the fire. The system consists of a gas turbine engine and afterburning system with injection of water, exit nozzle to produce the inert gas. It is generally known that the degree of oxygen content in the product of combustion depends on both inlet and outlet temperature of a combustor. Less the oxygen content in the combustion product higher will be the effectiveness of fire suppression. Injection of water brings additional advantages of suffocating and cooling effects which are both indespensable factors for fire suppressing. The special test rig was manufactured and experimental investigation of IGG system has been carried out. The automatic control system ensured stable operation of gas turbine engine and afterburner, water injection, fuel control and others. During the investigation the main parameters of gas turbine engine and auxiliarly systems were measured: gas temperature and pressure at gas turbine and afterburner exit, fuel flow rate, water mass flow rate, inlet air temperature, water temperature in the cooling chamber, mass flow rate, temperature and velocity of exhaust gas-steam mixture in the exit nozzle, oxygen content in the exit jet. The experimental investigation shows that developed IGG system can work very well for indoor fires but need some modifications in application to outdoor fire suppressing.

scholarly journals Theory of gas turbine engine optimal gas generator

2019 ◽  
Vol 18 (2) ◽  
pp. 52-61
Author(s):  
A. V. Grigoriev ◽  
A. A. Kosmatov ◽  
О. A. Rudakov ◽  
A. V. Solovieva
Keyword(s):  
Combustion Chamber ◽  
Gas Turbine ◽  
Gas Flow ◽  
Turbine Blades ◽  
Target Function ◽  
Gas Turbine Engine ◽  
Gas Generator ◽  
Joint Operation ◽  
Turbine Engine ◽  
Wide Range

The article substantiates the necessity of designing an optimal gas generator of a gas turbine engine. The generator is to provide coordinated joint operation of its units: compressor, combustion chamber and compressor turbine with the purpose of reducing the period of development of new products, improving their fuel efficiency, providing operability of the blades of a high-temperature cooled compressor turbine and meeting all operational requirements related to the operation of the optimal combustion chamber including a wide range of stable combustion modes, high-altitude start at subzero air and fuel temperature conditions and prevention of the atmosphere pollution by toxic emissions. Methods of optimizing the parameters of coordinated joint operation of gas generator units are developed. These parameters include superficial flow velocities in the boundary interface cross sections between the compressor and the combustion chamber, as well as between the combustion chamber and the compressor turbine. The effective efficiency of the engine thermodynamic cycle is the optimization target function. The required depth of the turbine blades cooling is a functional constraint evaluated with account for calculations of irregularity and instability of the gas temperature field and the actual flow turbulence intensity at the blades’ inlet. We carried out theoretical analysis of the influence of various factors on the gas flow that causes changes in the flow total pressure in the channels of the gas generator gas dynamic model, i.e. changes in the efficiencies of its units. It is shown that the long period (about five years) of the engine final development time, is due to the necessity to perform expensive full-scale tests of prototypes, in particular, it is connected with an incoordinate assignment in designing the values of the flow superficial velocities in the boundary sections between the gas generator units. Designing of an optimal gas generator is only possible on the basis of an integral mathematical model of an optimal combustion chamber.

A Parametric Starting Study of an Axial-Centrifugal Gas Turbine Engine Using a One-Dimensional Dynamic Engine Model and Comparisons to Experimental Results: Part II—Simulation Calibration and Trade-Off Study

1999 ◽  
Vol 121 (3) ◽  
pp. 384-393 ◽  
Author(s):  
A. K. Owen ◽  
A. Daugherty ◽  
D. Garrard ◽  
H. C. Reynolds ◽  
R. D. Wright
Keyword(s):  
Gas Turbine ◽  
Initial Conditions ◽  
Model Development ◽  
Gas Turbine Engine ◽  
Calibration Data ◽  
Gas Generator ◽  
Trade Off ◽  
Turbine Engine ◽  
One Dimensional ◽  
Engine Model

A generic one-dimensional gas turbine engine model, developed at the Arnold Engineering Development Center, has been configured to represent the gas generator of a General Electric axial-centrifugal gas turbine engine in the six-kg/sec airflow class. The model was calibrated against experimental test results for a variety of initial conditions to insure that the model accurately represented the engine over the range of test conditions of interest. These conditions included both assisted (with a starter motor) and unassisted (altitude windmill) starts. The model was then exercised to study a variety of engine configuration modifications designed to improve its starting characteristics and thus quantify potential starting improvements for the next generation of gas turbine engines. This paper presents the model calibration results and the results of the trade-off study. A companion paper discusses the model development and describes the test facilities used to obtain the calibration data.

Investigation of Bending Stiffness of Gas Turbine Engine Rotor Flanged Connection

2020 ◽  
Vol 36 (6) ◽  
pp. 729-736
Author(s):  
F.R. Nizametdinov ◽  
Yu.S. Romashin ◽  
A.L. Berne ◽  
M.K. Leontyev
Keyword(s):  
Gas Turbine ◽  
Nonlinear Function ◽  
Bending Moment ◽  
Gas Turbine Engine ◽  
Bending Stiffness ◽  
Gas Generator ◽  
Turbine Engine ◽  
Tightening Force ◽  
Flange Connection ◽  
Stiffness Properties

ABSTRACTThe article deals with the modeling of stiffness properties of the rotors flange joints, which largely determine overall dynamics. Research is conducted on the example of the standard compressor shaft flange connection and the disk of the high-pressure turbine in the gas generator of the gas turbine engine (GTE). It is noted that the bending stiffness of the flange connection is a nonlinear function of the bending moment, whose both experimental and analysis magnitude is related to the rotor deflection from the unbalanced forces. It is shown that the value of the bending stiffness essentially depends not upon the flange connection geometry but on the bolts tightening force, the axial force, the tensile joint, the contact strain of the flange surfaces. Analysis of the effect obtained in different models of the flange connection of the bending stiffness values on the overall dynamics of the rotor showed the necessity of taking into account the entire set of factors acting in the joint.

scholarly journals ЕФЕКТИВНА ТЯГА ТА ЗОВНІШНІЙ ОПІР АВІАЦІЙНОЇ СИЛОВОЇ УСТАНОВКИ

2020 ◽  
pp. 61-67
Author(s):  
Юрий Юрьевич Терещенко ◽  
Иван Алексеевич Ластивка ◽  
Павел Владимирович Гуменюк ◽  
Су Хунсян
Keyword(s):  
Power Plant ◽  
Gas Turbine ◽  
Power Plants ◽  
Gas Turbine Engine ◽  
Turbine Engines ◽  
Gas Generator ◽  
External Resistance ◽  
Turbine Engine ◽  
Engine Thrust ◽  
Engine Nacelle

Increasing the efficiency and effectiveness of a gas turbine engine can be achieved through a comprehensive review of all tasks that determine the parameters and characteristics of an aircraft power plant and aircraft. An important place in this complex is occupied by the problem of obtaining the most efficient traction and power plant based on the integration of the parameters and characteristics of the nacelle and gas turbine engine, consisting of a universal gas generator module and a turbofan module. Reducing the negative impact of the engine nacelle module on effective traction and effective specific fuel consumption is an urgent problem that can be solved based on the results of studies of the integration parameters and characteristics of the engine nacelle of the gas generator module and the gas turbine engine with the turbine-fan extension module, namely, with the implementation of structurally layout diagram of a gas turbine engine with a modular design with a rear arrangement of a turbofan attachment. For modern power plants with bypass gas turbine engines with a large bypass ratio, the external resistance is 2-3 % of the engine thrust during cruising operation. The results of experimental studies have shown that the external resistance of power plants with bypass gas turbine engines of modern supersonic aircraft is 4-6 % of the engine thrust during cruising operation. The paper considers the issues of aerodynamic integration of a gas turbine engine and a nacelle of an aircraft power plant. Aerothermogasdynamic integration of a gas turbine engine and an aircraft provides for the coordination of the parameters of the working process and the characteristics of the gas turbine engine and the parameters and characteristics of the nacelle of the aircraft in order to obtain optimal parameters and characteristics of the aircraft in the design flight conditions. The dependences of the relative effective thrust on the flight velocity are obtained. The obtained dependencies show the influence of the external resistance of the engine nacelle on the effective thrust of the bypass engine at subsonic flight velocities. The calculations were performed to lengthen the nacelle in the range from 4 to 8.

scholarly journals A Parametric Starting Study of an Axial-Centrifugal Gas Turbine Engine Using a One-Dimensional Dynamic Engine Model and Comparisons to Experimental Results: Part 2 — Simulation Calibration and Trade-Off Study

1998 ◽  
Author(s):  
A. Karl Owen ◽  
Anne Daugherty ◽  
Doug Garrard ◽  
Howard C. Reynolds ◽  
Richard D. Wright
Keyword(s):  
Gas Turbine ◽  
Initial Conditions ◽  
Model Development ◽  
Gas Turbine Engine ◽  
Calibration Data ◽  
Gas Generator ◽  
Trade Off ◽  
Turbine Engine ◽  
One Dimensional ◽  
Engine Model

A generic one-dimensional gas turbine engine model, developed at the Arnold Engineering Development Center, has been configured to represent the gas generator of a General Electric axial-centrifugal gas turbine engine in the six-kg/sec airflow class. The model was calibrated against experimental test results for a variety of initial conditions to insure that the model accurately represented the engine over the range of test conditions of interest. These conditions included both assisted (with a starter motor) and unassisted (altitude windmill) starts. The model was then exercised to study a variety of engine configuration modifications designed to improve its starting characteristics and thus quantify potential starting improvements for the next generation of gas turbine engines. This paper presents the model calibration results and the results of the trade-off study. A companion paper discusses the model development and describes the test facilities used to obtain the calibration data.

scholarly journals Thermodynamic Design of a Small-Scale Gas Turbine Engine Family

2019 ◽  
pp. 41-53
Author(s):  
A.Yu. Tkachenko ◽  
V.N. Rybakov ◽  
E.P. Filinov ◽  
Ya.A. Ostapyuk
Keyword(s):  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Small Scale ◽  
Gas Generator ◽  
Turbine Plant ◽  
Turbine Engine ◽  
Engine Family ◽  
Work Cycle ◽  
Gas Turbine Plant ◽  
Cycle Parameter

The paper presents a procedure for selecting work cycle parameters and describes thermodynamic design of a small-scale gas turbine engine family consisting of a small-scale gas turbine engine and a gas turbine plant comprising a free turbine driving a power generator, on the basis of a standardized gas generator. In order to select reasonable work cycle parameter values for the small-scale gas turbine engine and gas turbine plant we used a non-linear optimisation technique accounting for functional and parametric constraints as implemented in the ASTRA CAE software. Calculation results allowed us to plot the locally optimal work cycle parameter regions for the small-scale gas turbine engine and gas turbine plant according to the efficiency criteria for both engines, which are specific fuel consumption and net energy conversion efficiency. Taking the constraints into account, we selected reasonable values for the standardized gas generator parameters within the compromise region obtained, specifically the turbine inlet temperature and compressor pressure ratio. Our quantitative results show how the efficiency indices decline in the engine family featuring a standardized gas generator as compared to engines equipped with individually tailored gas generators. Designing a standardized gas generator in advance makes it possible to decrease engine development costs and time, ensure a higher reliability and a lower cost of production.

Full Authority Digital Engine Controller for Marine Gas Turbine Engine

2006 ◽  
Author(s):  
B. Githanjali ◽  
P. Shobha ◽  
K. S. Ramprasad ◽  
K. Venkataraju
Keyword(s):  
Control System ◽  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Engine Fuel ◽  
Electronic Control ◽  
Gas Generator ◽  
Turbine Engine ◽  
Engine Control System ◽  
Control Units ◽  
Commercial Off The Shelf

A full authority digital engine control system (FADEC) has been configured for the marine gas turbine engine being developed at the Gas Turbine Research Establishment, Bangalore, India. This paper presents the development of a prototype FADEC for this aero-derivative marine gas turbine engine. A dual-redundant architecture, with two identical digital electronic control units (DECU) in an active-standby configuration, was chosen to provide the necessary reliability, availability and maintainability. The system provides automatic control of engine fuel flow and compressor variable geometry, without exceeding parameter limits, so as to control either the speed of the gas generator or the power turbine in order to meet the power demanded. While the control units incorporate hardware and software features to detect and accommodate faults, an independent electronic trip system was included as a part of the overall control system to handle those situations resulting in uncontrolled overspeeding or safety interlock requirements. Recognizing the global trend towards the use of commercial off the shelf (COTS) technology, the system was configured with industry proven hardware and software. In addition, a hydro-mechanical backup control provides limited operational capability in the event of electronic control failure.

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