GSP is a generic modelling tool capable of modelling virtually any gas turbine engine configuration including (external) loads (like water breaks, pumps, generators, etc). GSP is primarily based on 0D-modelling (zero-D) of the thermodynamic cycle of the gas turbine. This implies that the flow properties are averaged over the flow cross section areas at the interface surfaces of the component models (inlet and the exit). GSP utilizes component model stacking to create the thermodynamic cycle of the engine of interest. Input of the model configuration is the cycle design, or any known reference point (or preferably several points) of a new engine. Information needed for the cycle configuration, eg. turbine and compressor maps, is readily available from the manufacturer or from the internet (e.g. manufacturer fact sheets, ASME papers, etc.). Besides being a performance prediction tool, GSP is especially suitable for parameter sensitivity analysis such as: ambient (flight) condition effects analysis, installation (losses) effects analysis, analysis of effects of certain engine malfunctioning (including control system malfunctioning) and component deterioration effects analysis. Input for the analysis is based on the model configuration (e.g. fuel flow can be specified to calculate the generated power, or when the fuel flow is set as a state variable the power can be specified to calculate the corresponding fuel flow). By running the simulation, output data set in the component property window will be displayed in a table, which can be visualized by a build-in graph tool. Data available includes the gas conditions (temperatures, pressures, mass flows, areas, speeds, etc) and the gas composition (gas species are available since GSP uses a full Thermo-chemical gas properties model). The simulation results can be exported to tab separated files, which can then be used for custom analysis (e.g. comparison of simulation data to running equipment measured data).
The development of GSP started at the Delft Technical University (TUD, Aerospace dept.) in 1986. At TUD, NASA's DYNGEN (NASA TN D-7901, 1975) program was used for jet- and turbofan engine simulation. However, DYNGEN appeared to have many problems with numerical stability and had a poor user interface. As a consequence, GSP was developed, inheriting features from DYNGEN. Significant deficiencies of DYNGEN were fixed in GSP; especially the stability, the speed of the numerical iteration processes and the user interface were improved. It appeared that an additional amount of improvements, adjustments and extensions to the GSP program were necessary before useful simulation of a generic jet engine was possible. Development continued at NLR, where GSP has been converted first to FORTRAN77 and later when desktop computers gained computational power for acceptable prices to Borland Delphi(TM). Delphi allows rapid adaptation due to the use of object orientation, offering excellent means to maintain and extend the program. DYNGEN (1975)
unstable
slow
poor user interface
GSP in FORTRAN77 (1986)
thesis of W. Bouwmans at Delft University, Aerospace faculty
improved UI, solver, stability
practically usable
GSP for Windows (1996)
rapid development using Borland Delphi(TM)
Object Orientation / Object Oriented design
powerful user interface
Gas turbine simulation program
GSP's most interesting features are listed below Flexible
any kind of gas turbine configuration
steady-state and transient off-design simulation
NLR-developed custom components
user-developed custom components
object-orientation
user-configurable graphical & tabular output formats
backwards compatible
Powerful
high execution speed on standard PC's
multiple effects on performance
rapid analysis of complex problems
simultaneous simulation of multiple models (twin-engine helicopter)
user configurable control system logic
user configurable control over equation system
User-friendly
graphical user interface (MS-Windows)
drag & drop components or models
on-line help, user manual & technical manual
variety of graphical & tabular output formats
Component based
object-oriented architecture
0/1-dimensional modelling
custom components
Extended
various libraries with custom components
3rd party component development kit available (GSP CDP)
an application programming interface for interaction with other software (GSP API)
GasTurb 11 and the Gas Turbine Simulation Program (GSP) 11 are two commercially available gas turbine simulation programs used by industrial professionals and academic researchers throughout the world. The two programs use a pseudo-perfect gas assumption in their calculations, where the specific heat is taken as a function of temperature and gas composition but not pressure. This assumption allows the two programs to make more realistic calculations of gas turbine engine performance. This is in contrast to the ideal and perfect gas assumptions used in classroom calculations. In addition, GasTurb 11 and GSP 11 both utilize component maps, comprised from test data, to model off-design turbojet component behavior. This is different from the referencing technique where off-design performance is calculated based on the ratio of off-design to on-design conditions. This thesis presents a comparative study of the two simulation programs with the traditional ideal-perfect gas calculations and the referencing technique. The scope of the thesis is limited to the turbojet without afterburners.
As energy providers help combat climate change, gas turbine manufacturers can rise to the challenge by designing cleaner and more efficient equipment. To meet ambitious energy efficiency and sustainability targets set by gas turbine manufacturers, embracing digitalization is essential. Download our executive brief to learn how building a holistic digital twin with gas turbine simulation software enables improved gas turbine designs.
The world is facing new challenges on sustainability and global warming and, as a result, propulsion and power technologies will play an even greater role in shaping the future. The solution of these problems very often demands engineers who are versed in the latest know-how in system modeling and simulation. Aviation has been and is at the forefront in this respect, and the power sector has always benefited from such innovation. In this unique course, you will advance your system modeling skills, which are at the core of the design process and essential for predicting and evaluating performance.
Given an engineering problem related to propulsion and power systems, you will use the 9-step method to create or select the appropriate model and run and interpret simulations in order to obtain a good solution of such a problem, and communicate the results.
You will be guided by instructors during dedicated online sessions and, if you can participate in person, during practical workshops. You will be encouraged to collaborate with your peers, as you would do in a professional environment. You will use software tools including OpenModelica and GSP to develop and configure the models required to run the simulations for your specific analysis. You can choose an engineering problem related to an aero engine, industrial gas turbine or another energy system.
In addition, the student will apply these new techniques to become competent in more specific problems to be chosen among those involving aero engines, gas turbines, power and thermal control systems. To this end, teams of students will work on an assignment which requires them to develop a system model, run simulations, interpret results and write a short report. Specific learning objectives related to the practical part of the course are therefore:
If you successfully complete your online course you will be awarded a TU Delft certificate, stating that you were registered as a non-degree-seeking student at TU Delft and successfully completed the course. The certificate will also indicate the number of ECTS credits this course is equal to (5 ECTS) when this course is taken as part of a degree program at the university.
If you decide that you would like to apply to the full Master's program in Aerospace Engineering, you will need to go through the admission process as a regular MSc student. If you are admitted, you can then request an exemption for this course, which you completed as a non-degree-seeking student. The Board of Examiners will evaluate your request and will decide whether or not you are exempted.
Required prior knowledge A relevant BEng or BSc degree in a subject closely related to the content of the course or specialized program in question, such as aerospace engineering, aeronautical engineering, mechanical engineering, civil engineering or (applied) physics.
Expected Level of English English is the only language used in this online course. If your working language is not English or you have not participated in an educational program in English in the past, please ensure that your level of proficiency is sufficient to follow the course. TU Delft recommends an English level equivalent to one of the following certificates (given as an indication only; the actual certificates are not required for the admission process):
The ProDiMES tool is coded in the MATLAB environment and consists of the following functions: a) Engine Fleet Simulator (EFS) which emulates the collection of data at takeoff and cruise from a fleet of engines over their lifetime of use; b) User provided diagnostic solutions designed to process the simulated parameter histories produced by the EFS, and generate a diagnostic assessment for each engine; c) Software program which automatically evaluates and archives performance of diagnostic solutions against established metrics; and e) A set of blind test case data to enable the side-by-side comparison of diagnostic solutions developed by multiple users. 2ff7e9595c
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