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About GSPThe Gas turbine Simulation Program GSP, a component based modelling environment, is NLR’s primary tool for gas turbine engine performance analysis. GSP's flexible object-oriented architecture allows steady-state and transient simulation of any gas turbine configuration using a user-friendly drag & drop interface with on-line help running under MS-Windows. Gas turbine configurations are simulated by establishing a specific arrangement of engine component models in a model window (view an example model window).What is GSPGSP 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.

• Gas Turbine Simulation Program
• Gas Turbine Simulation Programmes Online
• Gas Turbine Simulation Software

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).

Gas Turbine Simulation Program

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).GSP historyThe 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.

The gas turbine engine is a complex assembly of a variety of components that are designed on the basis of aerothermodynamic laws. The design and operation theories of these individual components are complicated. The complexity of aerothermodynamic analysis makes it impossible to mathematically solve the optimization equations involved in various gas turbine cycles. When gas turbine engines were designed during the last century, the need to evaluate the engines performance at both design point and off design conditions became apparent.

Manufacturers and designers of gas turbine engines became aware that some tools were needed to predict the performance of gas turbine engines especially at off design conditions where its performance was significantly affected by the load and the operating conditions. Also it was expected that these tools would help in predicting the performance of individual components, such as compressors, turbines, combustion chambers, etc. At the early stage of gas turbine developments, experimental tests of prototypes of either the whole engine or its main components were the only method available to determine the performance of either the engine or of the components.

Gas Turbine Simulation Programmes Online

However, this procedure was not only costly, but also time consuming. Therefore, mathematical modelling using computational techniques were considered to be the most economical solution. The first part of this paper presents a discussion about the gas turbine modeling approach.

Gas Turbine Simulation Software

The second part includes the gas turbine component matching between the compressor and the turbine which can be met by superimposing the turbine performance characteristics on the compressor performance characteristics with suitable transformation of the coordinates. The last part includes the gas turbine computer simulation program and its philosophy. The computer program presented in the current work basically satisfies the matching conditions analytically between the various gas turbine components to produce the equilibrium running line. The computer program used to determine the following: the operating range (envelope) and running line of the matched components, the proximity of the operating points to the compressor surge line, and the proximity of the operating points at the allowable maximum turbine inlet temperature. Most importantly, it can be concluded from the output whether the gas turbine engine is operating in a region of adequate compressor and turbine efficiency.

Matching technique proposed in the current work used to develop a computer simulation program, which can be served as a valuable tool for investigating the performance of the gas turbine at off-design conditions. Also, this investigation can help in designing an efficient control system for the gas turbine engine of a particular application including being a part of power generation plant.