Design of a Transient Variable Cycle Turbine Engine Model for System Integration with Controls

2017 ◽  
Author(s):  
Robert Buettner ◽  
Rory A. Roberts ◽  
Mitch Wolff ◽  
Alireza Behbahani
Keyword(s):  
System Integration ◽  
Turbine Engine ◽  
Engine Model

An Efficient Transient Simulation Method for a Volume Dynamics Model

2018 ◽  
Author(s):  
Masahiro Kurosaki ◽  
Minoru Sasamoto ◽  
Kentaro Asaka ◽  
Keiko Nakamura ◽  
Daiki Kakiuchi
Keyword(s):  
Integration Method ◽  
Simulation Method ◽  
Euler Method ◽  
Test Model ◽  
Dynamics Model ◽  
Engine Operation ◽  
Turbine Engine ◽  
Engine Model ◽  
Influence Coefficients ◽  
Transient Simulations

This paper presents an efficient numerical integration method for a volume dynamics model in gas turbine engine transient simulations. It is a modified implicit Euler method that allows a time increment that would not be stable with the explicit Euler method. The Jacobian matrix of a nonlinear engine model is evaluated along the steady state engine operation line and scheduled as a function of the corrected shaft speed in advance, eliminating the necessity of computing during the simulation. The proposed method was applied to transient simulations of a compressor rig test model composed of a compressor, a nozzle with variable geometry and a volume placed between them. The eigenvalues of the simplified volume dynamics were analytically derived. It is shown that they are functions of the characteristic time of the volume defined by mass present in the volume divided by mass flow rate flowing into and out of the volume and dimensionless influence coefficients of nearby components.

New Model Based Gas Turbine Fault Diagnostics Using 1D Engine Model and Nonlinear Identification Algorithms

2009 ◽  
Author(s):  
Seyyed Hamid Reza Hosseini ◽  
Hiwa Khaledi ◽  
Mohsen Reza Soltani
Keyword(s):  
Gas Turbine ◽  
Diagnostic System ◽  
Gas Turbine Engine ◽  
Fault Model ◽  
Fault Identification ◽  
Identification System ◽  
Turbine Engine ◽  
Engine Model ◽  
Exhaust Temperature ◽  
Model Based

Gas turbine fault identification has been used worldwide in many aero and land engines. Model based techniques have improved isolation of faults in components and stages’ fault trend monitoring. In this paper a powerful nonlinear fault identification system is developed in order to predict the location and trend of faults in two major components: compressor and turbine. For this purpose Siemens V94.2 gas turbine engine is modeled one dimensionally. The compressor is simulated using stage stacking technique, while a stage by stage blade cooling model has been used in simulation of the turbine. New fault model has been used for turbine, in which a degradation distribution has been considered for turbine stages’ performance. In order to validate the identification system with a real case, a combined fault model (a combination of existing faults models) for compressor is used. Also the first stage of the turbine is degraded alone while keeping the other stages healthy. The target was to identify the faulty stages not faulty components. The imposed faults are one of the most common faults in a gas turbine engine and the problem is one of the most difficult cases. Results show that the fault diagnostic system could isolate faults between compressor and turbine. It also predicts the location of faulty stages of each component. The most interesting result is that the fault is predicted only in the first stage (faulty stage) of the turbine while other stages are identified as healthy. Also combined fault of compressor is well identified. However, the magnitude of degradation could not be well predicted but, using more detailed models as well as better data from gas turbine exhaust temperature, will enhance diagnostic results.

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.

Surge Margin Tracking for Active Control of Quick Windmill Relighting

2004 ◽  
Author(s):  
Sog-Kyun Kim ◽  
Ian A. Griffin ◽  
Haydn A. Thompson ◽  
Peter J. Fleming
Keyword(s):  
High Pressure ◽  
Active Control ◽  
Pressure Ratio ◽  
Flight Test ◽  
Operating Pressure ◽  
Turbine Engine ◽  
Engine Model ◽  
Surge Margin ◽  
Stator Vane ◽  
Compressor Map

Surge margin tracking logic is developed for use in the control of quick windmill relighting (QWR) at sub-idle. Using existing high pressure compressor (HPC) characteristics (but without any gas turbine engine model), the surge margin can be calculated and used to approximate the air flow which is currently not measured in flight. During the QWR flight test, only limited measurements excluding the airflow measurement are available. Based on the fact that a beta value is equivalent to the position of the throttle valve in a compressor test rig, the role of the beta value is here to interrelate between the PRC (pressure ratio of compressor) and NDMF (non-dimensional mass flow) values for the measured CNH (corrected high pressure spool speed) and PRC values. Using the proposed scaling factors (SFs), the HPC map in terms of PRC is adaptively scaled with the engine parameters to cover the operating pressure ratio of the HPC. These account qualitatively for the effects of heat soakage and stability aids such as bleed and VSV (variable stator vane) on the compressor map. The simulation results show that the variable SF approach is more realistic in estimation of the surge margin, compared to the fixed SF approach. As a result of this proposed surge margin tracking logic, an active control for QWR may be possible using an estimated surge margin to adjust the fuel flow. This improves the pull-away time to reach idle power without danger of stall or surge during QWR.

scholarly journals Application of Transient and Dynamic Simulations to the U.S. Army T55-L-712 Helicopter Engine

1996 ◽  
Author(s):  
S. A. Savelle ◽  
G. D. Garrard
Keyword(s):  
Time Dependent ◽  
Limited Information ◽  
Component Level ◽  
Dynamic Simulations ◽  
Engine Operation ◽  
Turbine Engine ◽  
One Dimensional ◽  
Engine Simulation ◽  
Engine Model ◽  
The U.S

The T55-L-712 turboshaft engine, used in the U.S. Army CH-47D Chinook helicopter, has been simulated using version 3.0 of the Advanced Turbine Engine Simulation Technique (ATEST) and version 1.0 of the Aerodynamic Turbine Engine Code (ATEC). The models simulate transient and dynamic engine operation from idle to maximum power and run on an IBM-compatible personal computer. ATEST is a modular one-dimensional component-level transient turbine engine simulation. The simulation is tailored to a specific engine using engine-specific component maps and an engine-specific supervisory subroutine that defines component interrelationships. ATEC is a one-dimensional, time-dependent, dynamic turbine engine simulation. ATEC simulates the operation of a gas turbine by solving the one-dimensional, time dependent Euler equations with turbomachinery source terms. The simulation uses elemental control volumes at the sub-component level (e.g. compressor stage). The paper discusses how limited information from a variety of sources was adapted for use in the T55 simulations and how commonality between the models allowed reuse of the same material. The first application of a new turbine engine model, ATEC, to a specific engine is also discussed. Calibration and operational verification of the simulations will be discussed, along with the status of the simulations.

Conversion of the AE 1107C From the V-22 Osprey Application to Marine Service

2013 ◽  
Author(s):  
Zechariah D. Green ◽  
Sean Padfield ◽  
Andrew F. Barrett ◽  
Paul G. Jones
Keyword(s):  
Gas Turbine ◽  
System Integration ◽  
Development Program ◽  
Gas Turbine Engine ◽  
Naval Vessel ◽  
Turbine Engine ◽  
The Us ◽  
Technical Risk ◽  
Turbine Design ◽  
System Designs

This paper presents a study on the conversion of the Rolls-Royce AE 1107C V-22 Osprey gas turbine engine into the MT7 Ship-to-Shore Connector (SSC) marine gas turbine engine. The US Navy led SSC design requires a propulsion and lift gas turbine rated at 5,230 shaft horsepower, which the AE 1107C variant MT7 is capable of providing with margin on power and specific fuel consumption. The MT7 leverages the AE family of engines to provide a propulsion and lift engine solution for the SSC craft. Extensive testing and analysis completed during the AE 1107C development program aided in the robust gas turbine design required to meet the needs of the SSC program. Requirements not met by the AE 1107C configuration were achieved with designs based on the AE family of engines and marine grade sub-system designs. Despite the fact that system integration and testing remain as key activities for integrating the MT7 with the SSC craft, conversion of the AE 1107C FAA certified engine into an American Bureau of Shipping Naval Vessel Rules Type Approved MT7 engine provides a low technical risk alternative for the demanding requirements of the SSC application.

A Gas Turbine Engine Model of Transient Operation Across the Flight Envelope

2011 ◽  
Author(s):  
Reza Rezvani ◽  
Metin Ozcan ◽  
Brian Kestner ◽  
Jimmy Tai ◽  
Dimitri N. Mavris ◽  
...  
Keyword(s):  
Neural Net ◽  
Transient Operation ◽  
Turbofan Engine ◽  
Turbine Engine ◽  
Engine Model ◽  
Complex Models ◽  
Model Execution ◽  
Transient Models ◽  
Fidelity Model ◽  
Good Agreement

This paper introduces a method to create engine transient models that retain the fidelity and non-linearity of complex models as well as simplicity and speed of lower fidelity linearized models. The method is based on the design of experiments (DOE) and neural network methodology to create an analytic non-linear model of engine transient operation which has the potential to be used in on-board and off-board applications. The feed forward neural net models were created for a high fidelity model of high bypass turbofan engine (truth model). The performance of the neural net models was verified against the truth model. The verification results showed good agreement between the output of the neural net models and the truth model. Initial investigations also showed a significant reduction in the model execution time.

Virtual Turbine Engine Test Bench Using MGET Test Device

2014 ◽  
Author(s):  
Seong Hee Kho ◽  
Ja Young Ki ◽  
Chang Duk Kong
Keyword(s):  
Real Time ◽  
Test Bench ◽  
Operating Costs ◽  
Extreme Conditions ◽  
Engine Test ◽  
Engine Test Bench ◽  
Test Device ◽  
Turbine Engine ◽  
Engine Model ◽  
Engine Maintenance

Test device using virtual engine simulator can help reduce the number of engine tests through tests similar to the actual engine tests and repeat the test under the same condition, and thus reduce the engine maintenance and operating costs [1]. Also, as it is possible to easily implement extreme conditions in which it is hard to conduct actual tests, it can prevent engine damages that may happen during the actual engine test under such conditions. In this study, an upgraded MGET test device was developed that can conduct both real and virtual engine test by applying real-time engine model to the existing MGET test device that was developed and has been sold by the Company. This newly developed multi-purpose MGET test device is expected to be used for various educational and research purposes.

A Real-Time Transient Model of CF6 Turbofan Engine

2012 ◽  
Vol 241-244 ◽  
pp. 1573-1585 ◽  
Author(s):  
Hua Ting Yao ◽  
Xi Wang ◽  
Xiang Xing Kong
Keyword(s):  
Real Time ◽  
Nonlinear Equations ◽  
Volume Effect ◽  
Open Loop ◽  
Transient Model ◽  
Turbine Engine ◽  
Engine Model ◽  
Iterative Model ◽  
The Stability ◽  
Stability And Accuracy

In traditional aeroengine modeling, the nonlinear equations of engine model are generally solved through iterative algorithm. However, due to the strong nonlinear characteristics of the equations, the iterative model often fails to converge at some points of the full envelope and has a poor real time performance. In order to solve the problems, this paper proposes a non-iterative modeling method based on volume effect. In this method, several variables and differential equations of volume dynamics in aeroengine are introduced to the nonlinear equations, as a result, the whole set of equations becomes closed-form and can be solved without iteration. The non-iterative model of a gas turbine engine is written in matlab code. Furthermore, an open-loop simulation is carried out in matlab/simulink, both under groud and altitude condition. Meanwhile, the non-iterative model is verified by GSP11. The results illustrate that the non-iterative model provides good performance both in the stability and accuracy of solutions.

GasTurboLib: Simulink Library for Gas Turbine Engine Modelling

2009 ◽  
Author(s):  
V. Panov
Keyword(s):  
Performance Analysis ◽  
Gas Turbine ◽  
Control Method ◽  
Cost Savings ◽  
System Stability ◽  
Turbine Engine ◽  
Engine Model ◽  
Modelling Environment ◽  
Engine Testing ◽  
User Friendly

A new Simulink library, called GasTurboLib, containing blocks specialized for gas turbine modelling has been developed. Different engine configurations can be generated using GasTurboLib components and these models can be used for steady state and transient performance analysis. This paper describes the newly developed generic gas turbine simulation tool and presents experiences with modelling and simulation of single and twin shaft gas turbine engines. This library enables 0-D modelling, which is the simplest level of modelling but the most widely used in industry. This component-based modelling environment can be used to simulate start-up sequence, load change, control system design, power-system stability studies and real-time modelling. Traditionally, control method improvements are developed and validated through engine testing. The goal was to develop a functional engine model, which can be started, operated and shut down by a governor model, for the purposes of development of control methods and protection algorithms, thus providing considerable cost savings, as well as enabling better project progress through independence from the availability of test beds. It has been demonstrated that rapid model generation and reusability of components along with user-friendly graphical user interface make this simulation environment a valuable tool for gas turbine system performance analysis.

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