Engine performance prediction for varied low pressure turbine vane geometry utilizing test rig data and combined computational fluid dynamic and cycle models This publication is based on the presentation, “Engine performance prediction for varied low pressure turbine vane geometry utilizing test rig data and combined computational fluid dynamic and cycle models”, that was presented at the ASME Turbo Expo 2012, 11-15 June 2012 in Copenhagen, Danmark. The publication describes the usage of CFD calculated map characteristics in a system modeling environment (GSP) to predict the expected engine performance, allowing a well-founded decision on acceptance of the refurbished vanes.

Performance Simulation of an ideal mixer-ejector turbofan engine for a supersonic business jet NLR's Gas Turbine Simulation Program (GSP) is used in this paper to carry out performance simulations for a so-called mixer-ejector engine variant for a supersonic businessjet. The mixer-ejector is used to reduce jet velocities and noise at take-off. The GSP mixer component has been modified to include the supersonic core flow. The papes shows the used methods and includes the simulations results. This publication is based on a presentation that was presented as ICAS-2010-4.9.2 at the ICAS 2010 Conference, 19-24 September 2009 in Nice, France.

Experience With GSP as a Gas Path Analysis Tool SKF's primary tool for gas turbine engine performance analysis is GSP (Gas turbine Simulation Program), a component based modeling environment that is developed at National Aerospace Laboratory NLR and Delft University of Technology, The Netherlands. One of the applications is gas path analysis (GPA) using GSP's generic adaptive modeling capability. With GSP, gas path analysis has been applied to different aero engines at several maintenance facilities. Additional functionalities have been developed to analyze multiple engine operating points and combine results of different adaptive modeling configurations automatically, resulting in more accurate and reliable GPA results. A ‘multi-point calibration’ method for the reference model was developed providing a significant improvement of GPA accuracy and stability. Also, a method was developed using ‘multiple analysis cycles’ on different condition indicator subsets, which successfully generated values for all condition parameters in cases with fewer measurement parameters than condition indicators and where measurement data are unreliable. The method has been successfully demonstrated on the GEM42 turbo shaft engine. A number of case studies have shown GPA results corresponding to available maintenance notes and inspection data. The extension of the GSP GPA tool with a database system provides a useful tool for analyzing engine history and comparison of analyzed component conditions throughout the fleet. When a large amount of analysis data is stored in the database, statistic analyses, trending and data mining can be performed. Also maintenance work scope effect on engine performance can be predicted. In this paper, the newly developed GSP gas path analysis functionalities are described and experiences and results with the GEM42 engine operational environment are presented.

TERTS, a Generic Real-Time Gas Turbine Simulation Environment NLR's 'Turbine Engine Real-Time Simulator' (TERTS) is a component-based real-time modelling environment for gas turbines derived from GSP. TERTS is a powerful real-time tool for analysis of effects of malfunctions of control systems and other sub-systems on performance in pilot-in-the-loop simulations. TERTS is implemented in the Matlab-Simulink environment, offering excellent means to develop separate component and subsystem (especially control system) models. From Simulink, C-code can be generated for direct implementation of the model in NLR's National Simulation Facility NSF.The publication is based on a presentation that was presented as ASME-2001-GT-446 at the ASME Turbo Expo 2001, 4-7 June 2001 in New Orleans, Louisiana, USA, and gives a comprehensive description of the TERTS environment and an illustrative example of an afterburning turbofan.

Integrated lifing analysis tool for gas turbine components NLR has developed a method to predict gas turbine component life based on analysis of engine performance. Engine performance history is obtained from in-flight monitored engine parameters and flight conditions, and processed off-line by a combination of tools. Besides GSP as comprehensive thermodynamical engine system model, this combination includes models for heat transfer, thermal load, mechanical load and life consumption. Due to the relative high inaccuracy of the life consumption model component life can only be predicted relative to a reference life. This publication is based on a presentation that was presented as ASME-2000-GT-646 at the ASME Turbo Expo 2000, 8-11 May 2000 in Munich, Germany, and gives a comprehensive description of the application of GSP in an integrated tool. The tool is demonstrated with an analysis of deterioration effects on the life consumption of the F100PW220 engine 1st stage LPT rotor blade during a recorded RNLAF F-16 mission.