A model for combustor dynamics for inclusion in a dynamic gas turbine engine simulation code

1997 ◽  
Author(s):  
David Costura ◽  
Tomas Velez ◽  
Patrick Lawless ◽  
Steven Frankel ◽  
David Costura ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Simulation Code ◽  
Turbine Engine ◽  
Engine Simulation

Extensible object model for gas turbine engine simulation

2001 ◽  
Vol 21 (1) ◽  
pp. 111-118 ◽  
Author(s):  
Zhiwu Xie ◽  
Ming Su ◽  
Shilie Weng
Keyword(s):  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Object Model ◽  
Turbine Engine ◽  
Engine Simulation

An Integrated Approach for Gas Turbine Engine Simulation

2000 ◽  
Author(s):  
Zhiwu Xie ◽  
Ming Su ◽  
Shilie Weng
Keyword(s):  
Gas Turbine ◽  
Local Area Network ◽  
Integrated Approach ◽  
Local Area ◽  
Gas Turbine Engine ◽  
Future Research ◽  
Area Network ◽  
Turbine Engine ◽  
Engine Simulation ◽  
Engine Components

Abstract The static and transient performance of a gas turbine engine is determined by both the characteristics of the engine components and their interactions. This paper presents a generalized simulation framework that enables the integration of different component and system simulation codes. The concept of engine simulation integration and its implementation model is described. The model is designed as an object-oriented system, in which various simulation tasks are assigned to individual software components that interact with each other. A new design rationale called “message-based modeling” and its resulting class structure is presented and analyzed. The object model is implemented within a heterogeneous network environment. To demonstrate its flexibility, the codes that deal with different engine components are separately programmed on different computers running various operating systems. These components communicate with each other via a CORBA compliant ORB, which simulates the overall performance of an engine system. The resulting system has been tested on a Local Area Network (LAN) to simulate the transient response of a three-shaft gas turbine engine, subject to small fuel step perturbations. The simulation results for various network configurations are presented. It is evident that in contrast to a standalone computer simulation, the distributed implementation requires much longer simulation time. This difference of simulation efficiency is analyzed and explained. The limitations of this endeavor, along with some future research topics, are also reported in this paper.

scholarly journals Improving Dynamic Response of a Single-Spool Gas Turbine Engine Using a Nonlinear Contoller

1992 ◽  
Author(s):  
O. F. Qi ◽  
N. R. L. Maccallum ◽  
P. J. Gawthrop
Keyword(s):  
Dynamic Response ◽  
Gas Turbine ◽  
Linear Models ◽  
Digital Simulation ◽  
Gas Turbine Engine ◽  
Open Loop ◽  
Nonlinear Controller ◽  
Nonlinear Simulation ◽  
Turbine Engine ◽  
Engine Simulation

This paper describes the design of a closed-loop nonlinear controller to improve the dynamic response of a single-spool gas turbine engine. The nonlinear controller is obtained by scheduling the gains of multivariable compensators as a function of engine non-dimensional shaft speed. The compensators, whose outputs are fuel flow and nozzle area, are designed using optimal control theory based on a set of linear models generated from a nonlinear engine simulation. Investigations are also made into developing simple algorithms to obtain an analytical expression for the compressor given its characteristic. The detailed process of developing a nonlinear simulation model for the engine is also described. The open-loop fuel controller is studied using the digital simulation.

scholarly journals A Simplified Gas Turbine Engine Model With Heat Storage/Tip Clearance Effects

1993 ◽  
Author(s):  
T. H. Wong
Keyword(s):  
Gas Turbine ◽  
Heat Storage ◽  
Gas Turbine Engine ◽  
Tip Clearance ◽  
Metal Temperature ◽  
Transient Method ◽  
Transient Responses ◽  
Turbine Engine ◽  
Engine Simulation ◽  
Engine Model

A simplified turboshaft gas turbine engine model called the direct transient method (DTM) model has been developed. The DTM model consists of table look-up data generated from the actual engine data or the transient engine simulation. The DTM model accounts for heat storage, tip clearance and volume dynamics effects. It can, therefore, better predict engine transient responses and turbine metal temperature than the traditional engine horsepower extraction (HPX) model. This paper presents in detail the DTM methodology for generating accurate simplified engine models of transient performance. Comparisons of engine transient responses between the DTM and HPX models are provided.

scholarly journals Integrated Turbine Tip Clearance and Gas Turbine Engine Simulation

2016 ◽  
Author(s):  
Jeffryes W. Chapman ◽  
Ten-Huei Guo ◽  
Jonathan L. Kratz ◽  
Jonathan S. Litt
Keyword(s):  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Tip Clearance ◽  
Turbine Engine ◽  
Engine Simulation

scholarly journals Development of a Throughflow-Based Simulation Tool for Preliminary Compressor Design Considering Blade Geometry in Gas Turbine Engine

2021 ◽  
Vol 11 (1) ◽  
pp. 422
Author(s):  
Xiaoheng Liu ◽  
Ke Wan ◽  
Donghai Jin ◽  
Xingmin Gui
Keyword(s):  
Gas Turbine ◽  
Pressure Ratio ◽  
Gas Turbine Engine ◽  
Navier Stokes ◽  
Simulation Tool ◽  
Turbine Engine ◽  
Engine Simulation ◽  
Force Modeling ◽  
Dynamics Calculation ◽  
Improved Model

Gas turbine engines are highly intricate machines, and every component of them is closely associated with one another. In the traditional engine developing process, vast experiment tests are needed. To reduce unnecessary trials, a whole gas turbine engine simulation is extremely needed. For this purpose, a compressor simulation tool is now developed. Considering the inherent drawbacks of 0D analysis and 3D CFD (Computational Fluid Dynamics) calculation, the 2D throughflow method is an indispensable tool. Based on the circumferential average method (CAM), 3D Navier–Stokes is transformed into a 2D method. One phenomenon arising is that the lack of description about circumferential motion leads to the need for the blade force modeling in compressor simulation. Previous models are based on the assumption that flow passes through the average stream surface without entropy increasing, which is not applicable in the CAM. An improved model is proposed based on the result analysis from CAM and NUMECA method in a linear cascade. Whereafter, the model is applied in a highly loaded and low-speed fan, which has been tested for its performance characteristics. Utilizing the new model, the error of the adiabatic efficiency between CAM and experiment decreases from 4.0% to 1.0% and the accuracy of the mass flow, and pressure ratio remains unchanged. The time involved in the CAM simulation is nearly 70 times faster than that of the 3D simulation.

The ultra-high efficiency gas turbine engine, uhegt, part III: Dynamic behavior of the system in variable performance conditions

2021 ◽  
pp. 095765092110162
Author(s):  
Seyed M Ghoreyshi ◽  
Meinhard T Schobeiri
Keyword(s):  
Gas Turbine ◽  
Dynamic Behavior ◽  
Dynamic Simulation ◽  
High Efficiency ◽  
Time Lag ◽  
Combustion Process ◽  
Gas Turbine Engine ◽  
Simulation Code ◽  
Turbine Engine ◽  
Fuel Flow

This paper investigates the dynamic behavior of an Ultra-High Efficiency Gas Turbine Engine (UHEGT) with Stator Internal Combustion. The UHEGT-technology was introduced for the first time to the gas turbine design community at the Turbo Expo 2015. In developing the UHEGT-technology, the combustion process is no longer contained in isolation between the compressor and turbine, rather distributed in the first three HP-turbine stator rows. Noticeable improvement in the engine thermal efficiency and power along with other performance advantages are brought by this technology. In the current paper, dynamic simulation is performed on the entire gas turbine engine (UHEGT) using the nonlinear dynamic simulation code GETRAN. The simulations are in 2 D (space-time) and include the majority of the engine components including rotor shaft, turbine and compressor, fuel injectors, diffuser, pipes, valves, controllers, etc. The thermo-fluid conservation laws are applied to the flow in each component which create a system of nonlinear partial differential equations that is solved numerically. Two different fuel schedules (steep rise and Gaussian) are applied to all injectors and the engine response is studied in each case. The results show that fluctuations in the fuel flow lead to fluctuations in most of the system parameters such as temperatures, power, shaft speed, etc. However, the shapes and amplitudes of the fluctuations are different and there is a time lag in the response profiles relative to the fuel schedules. It is shown that an increase in average fuel flow in the system leads to a small drop in efficiency due to the cycle change from the design point. Moreover, it is seen that the temperatures usually rise fast with increase of fuel flow, but the system tends to cool down at a slower rate as the fuel is reduced.

scholarly journals Advances in Nonlinear Dynamic Engine Simulation With an Example: Dynamic Performance Behavior of a Gas Turbine With One Reheat Turbine Stage and Two Combustion Chambers

1996 ◽  
Author(s):  
M. T. Schobeiri ◽  
M. S. Attia
Keyword(s):  
Power Generation ◽  
Gas Turbine ◽  
Dynamic Simulation ◽  
Nonlinear Dynamic ◽  
Gas Turbine Engine ◽  
Full Scale ◽  
Turbine Stage ◽  
Combustion Chambers ◽  
Turbine Engine ◽  
Engine Simulation

The paper discusses some recent advances in dynamic engine simulation technology. A brief presentation of the physical background is followed by a detailed description of the turbine component, its modular representation, and its integration into the nonlinear dynamic engine simulation code GETRAN. In order to ensure the capability, accuracy, robustness, and reliability of the turbine module in interaction with GETRAN, comprehensive critical performance assessment and validation tests were performed. Two conceptually different engine configurations were dynamically simulated and their transient behavior was analyzed and compared with each other. As the first example, a full scale dynamic simulation of an advanced high performance single spool single shaft power generation gas turbine engine is presented. The second example includes the full scale dynamic simulation of an advanced power generation gas turbine engine with a reheat turbine stage and two combustion chambers. The comparison of these engines shows clearly the impact of the dynamic operation on the performance of individual gas turbine engines under consideration.

A Methodology for Fully-Coupled CFD Engine Simulations, Applied to a Micro Gas Turbine Engine

2018 ◽  
Author(s):  
Mateus Teixeira ◽  
Luigi Romagnosi ◽  
Mohamed Mezine ◽  
Yannick Baux ◽  
Jan Anker ◽  
...  
Keyword(s):  
Combustion Chamber ◽  
Gas Turbine ◽  
Cfd Simulation ◽  
Integrated Approach ◽  
Gas Turbine Engine ◽  
Flamelet Model ◽  
Turbine Engine ◽  
Micro Gas Turbine ◽  
Engine Simulation ◽  
Fully Coupled

The development of new generations of aircraft engines with reduced environmental impact heavily relies on high-fidelity 3D numerical analysis of the main engine components, compressor, combustion chamber, turbine and their interactions, including the transient and off-design behavior of the full engine. Unlike component-by-component analysis, which requires separate assumptions for the pressure and temperature boundary conditions for each component, a fully coupled approach requires only knowledge of the compressor inlet and turbine outlet flow conditions. In addition, the engine rotation speed can also be varied during the simulation to converge to the correct balance of power between compressor and turbine. This integrated approach provides a detailed description of the flow field inside the full engine at the desired operating point with one single CFD simulation. The full engine simulation methodology can be developed at several levels: (1) RANS simulations with mixing-plane interfaces between components; (2) advanced RANS treatment with inputs from the nonlinear harmonic (NLH) methodology to allow for tangential non-uniformity, such as hot streaks entering the turbine nozzle from the combustor; (3) inclusion of the unsteady rotor-stator interactions, via NLH, in compressor and turbine stages; (4) coupling with LES simulations in the combustor. This paper presents results from levels (1) and (2) of this methodology applied to a micro-turbine gas engine including the HP compressor, combustor, HP and LP turbines and the exhaust hood. The geometry has been obtained from the redesign of the KJ66 micro gas turbine engine using preliminary design tools. The injection and burning of fuel inside the combustion chamber are modeled with a simplified flamelet model. The paper presents the approach and results of the full engine simulation; as well as the initial steps towards level (3).

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