scholarly journals The Potential of a Multi-Fidelity Approach to Gas Turbine Combustor Design Optimization

2020 ◽  
Author(s):  
David Toal ◽  
Xu Zhang ◽  
Andy J. Keane ◽  
Chin Yik Lee ◽  
Marco Zedda
Keyword(s):  
Design Optimization ◽  
Gas Turbine ◽  
Design Process ◽  
Relative Cost ◽  
Gas Turbine Combustor ◽  
Surrogate Modelling ◽  
Simulation Fidelity ◽  
Industrial Setting ◽  
The Cost ◽  
Modelling Approach

Abstract The desire to reduce gas turbine emissions drives the use of design optimization approaches within the combustor design process. However, the relative cost of combustion simulations can prohibit such optimizations from being carried out within an industrial setting. Strategies which can significantly reduce the cost of such studies can enable designers to further improve emissions performance. The following paper investigates the application of a multi-fidelity surrogate modelling approach to the design optimization of a typical gas turbine combustor from a civil airliner engine. Results over three different case studies of varying problem dimensionality indicate that a multi-fidelity surrogate modelling based design optimization, whereby the simulation fidelity is varied by adjusting the coarseness of the mesh, can indeed improve optimization performance. These results indicate that such an approach has the potential to significantly reduce design optimization cost whilst achieving similar, or in some cases superior, design performance.

Preliminary Multidisciplinary Design Optimization System: A Software Solution for Early Gas Turbine Conception

2005 ◽  
Author(s):  
Pascal Prado ◽  
Yulia Panchenko ◽  
Jean-Yves Tre´panier ◽  
Christophe Tribes
Keyword(s):  
Design Optimization ◽  
Gas Turbine ◽  
Design Process ◽  
Multidisciplinary Design Optimization ◽  
Software Tool ◽  
Multidisciplinary Design ◽  
Engine Design ◽  
Wide Range ◽  
Speed Up ◽  
Turbine Design

Preliminary Multidisciplinary Design Optimization (PMDO) project addresses the development and implementation of the Multidisciplinary Design Optimization (MDO) methodology in the Concept/Preliminary stages of the gas turbine design process. These initial phases encompass a wide range of coupled engineering disciplines. The PMDO System is a software tool intended to integrate existing design and analysis tools, decompose coupled multidisciplinary problems and, therefore, allow optimizers to speed-up preliminary engine design process. The current paper is a brief presentation of the specifications for the PMDO System as well as a description of the prototype being developed and evaluated. The current assumed e xible architecture is based on three software components that can be installed on different computers: a Java/XML MultiServer, a Java Graphical User Interface and a commercial optimization software.

An Experimental Study on Modeling of Fuel Atomization for Simulating the Idle Regime of a Gas Turbine Combustor by Atmospheric Testing

1997 ◽  
Author(s):  
Yeoung Min Han ◽  
Min Soo Yoon ◽  
Woo Seok Seol ◽  
Dae Sung Lee ◽  
Victor I. Yagodkin ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Diagnostic Methods ◽  
Fuel Spray ◽  
Main Stage ◽  
Gas Turbine Combustor ◽  
Spray Characteristics ◽  
Fuel Atomization ◽  
Fuel Nozzle ◽  
Loading Parameter ◽  
The Cost

An experimental investigation is carried out on modeling of fuel atomization for the purpose of simulating the idle regime of a gas turbine combustor through atmospheric testing. If the simulation is successfully applied, it will significantly reduce the cost of testing. The simulation must sustain nearly the same fuel spray characteristics and the same aerodynamics at the exit of the frontal device. Air assisting through the main stage of a dual orifice fuel nozzle is employed to match the fuel spray characteristics. Optical diagnostic methods including flow visualization and Adaptive Phase/Doppler Velocimetry are used for the investigation of spray characteristics. Once the fuel spray characteristics are matched by air assisting, the combustor characteristics may then be matched by maintaining the loading parameter constant. The possibility of modeling with air assisting is shown and appropriate conditions for air assisting are found.

Micro Gas Turbine Combustor Emissions Evaluation Using the Chemical Reactor Modelling Approach

2007 ◽  
Author(s):  
Carmine Russo ◽  
Giulio Mori ◽  
Vyacheslav V. Anisimov ◽  
Joa˜o Parente
Keyword(s):  
Natural Gas ◽  
Gas Turbine ◽  
Atmospheric Pressure ◽  
Chemical Reactor ◽  
Exhaust Emissions ◽  
Operating Conditions ◽  
Gas Turbine Combustor ◽  
Micro Gas Turbine ◽  
Simulation Results ◽  
Modelling Approach

Chemical Reactor Modelling approach has been applied to evaluate exhaust emissions of the newly designed ARI100 (Patent Pending) recuperated micro gas turbine combustor developed by Ansaldo Ricerche SpA. The development of the chemical reactor network has been performed based on CFD reacting flow analysis, obtained with a global 2-step reaction mechanism, applying boundary conditions concerning the combustion chamber at atmospheric pressure, with 100% of thermal load and fuelled with natural gas. The network consists of 11 ideal reactors: 6 perfectly stirred reactors, and 5 plug flow reactors, including also 13 mixers and 12 splitters. Simulations have been conducted using two detailed reaction mechanisms: GRI Mech 3.0 and Miller & Bowman reaction mechanisms. Exhaust emissions have been evaluated at several operating conditions, obtained at different pressure, and considering different fuel gases, as natural gas and a high H2 content SYNGAS fuel. Furthermore, emissions at different thermal loads have been investigated when natural gas at atmospheric pressure is fuelled. Simulation results have been compared with those obtained from combustion experimental campaign. CO and NOx emissions predicted with CRM approach closely match experimental results at representative operating conditions. Ongoing efforts to improve the proposed reactors network should allow extending the range of applicability to those operating conditions whose simulation results are not completely satisfying. Given the small computational effort required, and the accuracy in predicting combustor experimental exhaust emissions, both CO and NOx, the CRM approach turnout to be an efficient way to reasonably evaluate exhaust emissions of a micro gas turbine combustor.

scholarly journals Integrated uncertainty techniques in aircraft derivative design optimization.

2021 ◽  
Author(s):  
Hyeong-Uk Park
Keyword(s):  
Sensitivity Analysis ◽  
Design Optimization ◽  
Design Process ◽  
Aircraft Design ◽  
Collaborative Optimization ◽  
Aircraft Manufacturing ◽  
Analysis Tools ◽  
Design Variables ◽  
The Cost ◽  
Aircraft Conceptual Design

Aircraft manufacturing companies have to consider multiple derivatives to satisfy various market requirements. They modify or extend an existing aircraft to meet the new market demands while keeping the development time and the cost to a minimum. Many researchers have studied the derivative design process, but these research considered the baseline and the derivatives together, while using the whole set of design variables. Therefore, an efficient process that can reduce the cost and the time for the aircraft derivative design is needed. In this dissertation, Aircraft Derivative Design Optimization process (ADDOPT) was developed which obtains the global changes from the local changes in the aircraft design to develop the aircraft derivatives efficiently. The sensitivity analysis was implemented to ignore design variables that have low impact on the objective function. This avoids wasting computational effort and time on low priority variables for design requirements and objectives. Additionally, the classification of uncertainty from its characteristics and sources of uncertainty involved in the aircraft design process were suggested to consider with design optimization. Uncertainty from the fidelity of analysis tools was applied in design optimization to increase the probability of optimization results. To handle uncertainty in low fidelity analysis tools on aircraft conceptual design optimization, Reliability Based Design Optimization (RBDO) and Possibility Based Design Optimization (PBDO) methods were performed. In this research, Extended Fourier Amplitude Sensitivity Test (eFAST) method was implemented in ADDOPT for Global Sensitivity Analysis (GSA) method and Collaborative Optimization (CO) based framework with RBDO and PBDO were also used. These methods were evaluated using numerical examples. ADDOPT was carried through on the civil jet aircraft derivative design. The objective of the optimization problem was to increase cruise range while satisfying the requirement such as the number of passengers. The proposed process reduced computation effort by reducing the number of design variables and achieved the target probability of failure when considering uncertainty from low fidelity analysis tools.

scholarly journals Integrated uncertainty techniques in aircraft derivative design optimization.

2021 ◽  
Author(s):  
Hyeong-Uk Park
Keyword(s):  
Sensitivity Analysis ◽  
Design Optimization ◽  
Design Process ◽  
Aircraft Design ◽  
Collaborative Optimization ◽  
Aircraft Manufacturing ◽  
Analysis Tools ◽  
Design Variables ◽  
The Cost ◽  
Aircraft Conceptual Design

Aircraft manufacturing companies have to consider multiple derivatives to satisfy various market requirements. They modify or extend an existing aircraft to meet the new market demands while keeping the development time and the cost to a minimum. Many researchers have studied the derivative design process, but these research considered the baseline and the derivatives together, while using the whole set of design variables. Therefore, an efficient process that can reduce the cost and the time for the aircraft derivative design is needed. In this dissertation, Aircraft Derivative Design Optimization process (ADDOPT) was developed which obtains the global changes from the local changes in the aircraft design to develop the aircraft derivatives efficiently. The sensitivity analysis was implemented to ignore design variables that have low impact on the objective function. This avoids wasting computational effort and time on low priority variables for design requirements and objectives. Additionally, the classification of uncertainty from its characteristics and sources of uncertainty involved in the aircraft design process were suggested to consider with design optimization. Uncertainty from the fidelity of analysis tools was applied in design optimization to increase the probability of optimization results. To handle uncertainty in low fidelity analysis tools on aircraft conceptual design optimization, Reliability Based Design Optimization (RBDO) and Possibility Based Design Optimization (PBDO) methods were performed. In this research, Extended Fourier Amplitude Sensitivity Test (eFAST) method was implemented in ADDOPT for Global Sensitivity Analysis (GSA) method and Collaborative Optimization (CO) based framework with RBDO and PBDO were also used. These methods were evaluated using numerical examples. ADDOPT was carried through on the civil jet aircraft derivative design. The objective of the optimization problem was to increase cruise range while satisfying the requirement such as the number of passengers. The proposed process reduced computation effort by reducing the number of design variables and achieved the target probability of failure when considering uncertainty from low fidelity analysis tools.

scholarly journals Assessment of Combustor Working Environments

2012 ◽  
Vol 2012 ◽  
pp. 1-6 ◽  
Author(s):  
Leiyong Jiang ◽  
Andrew Corber
Keyword(s):  
Gas Turbine ◽  
Operating Conditions ◽  
Reacting Flow ◽  
Gas Turbine Combustor ◽  
Two Phase ◽  
Turbine Engine ◽  
Working Environments ◽  
Flow Features ◽  
Critical Components ◽  
The Cost

In order to assess the remaining life of gas turbine critical components, it is vital to accurately define the aerothermodynamic working environments and service histories. As a part of a major multidisciplinary collaboration program, a benchmark modeling on a practical gas turbine combustor is successfully carried out, and the two-phase, steady, turbulent, compressible, reacting flow fields at both cruise and takeoff are obtained. The results show the complicated flow features inside the combustor. The airflow over each flow element of the combustor can or liner is not evenly distributed, and considerable variations, ±25%, around the average values, are observed. It is more important to note that the temperatures at the combustor can and cooling wiggle strips vary significantly, which can significantly affect fatigue life of engine critical components. The present study suggests that to develop an adequate aerothermodynamics tool, it is necessary to carry out a further systematic study, including validation of numerical results, simulations at typical engine operating conditions, and development of simple correlations between engine operating conditions and component working environments. As an ultimate goal, the cost and time of gas turbine engine fleet management must be significantly reduced.

PHASE DOPPLER PARTICLE SIZING INSIDE A PRODUCTION GAS TURBINE COMBUSTOR

1994 ◽  
Vol 3 (1-6) ◽  
pp. 301-312 ◽  
Author(s):  
R. Kneer ◽  
M. Willmann ◽  
R. Zeitler ◽  
S. Wittig ◽  
K.-H. Collin
Keyword(s):  
Gas Turbine ◽  
Particle Sizing ◽  
Gas Turbine Combustor
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