S. Woldendorp - Academia.edu (original) (raw)
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Papers by S. Woldendorp
Analysis of combined convective and film cooling on an existing turbine blade W.B. de Wolf, S. Wo... more Analysis of combined convective and film cooling on an existing turbine blade W.B. de Wolf, S. Woldendorp and T. Tinga This report is based on a presentation held at the RTO-AVT Symposium on Heat Transfer
To support gas turbine operators, NLR is developing capabilities for life assessment of hot engin... more To support gas turbine operators, NLR is developing capabilities for life assessment of hot engine components. As a typical example the first rotor blades of the high pressure (HP) turbine of the FlOO- PW-220 military turbofan will be discussed. For these blades tools have been developed to derive the blade temperature history from flight data obtained from F-16 missions. The resulting relative life consumption estimate should support the Royal Netherlands Air Force in their engine maintenance activities. The present paper describes the prediction method for the blade temperature, based on reverse engineering. Input data are the flight data of the engine performance parameters and the geometry of the HP turbine blades and vanes including film cooling orifices. The engine performance parameters are converted in HP turbine entry and exit conditions by the NLR Gas Turbine Simulation Program (GSP) engine model. Next a Computational Fluid dynamics (CFD) tool is used to calculate the resu...
A method to predict gas turbine component life based on engine performance analysis is demonstrat... more A method to predict gas turbine component life based on engine performance analysis is demonstrated on a hot section gas turbine component. The mechanical and thermal loading of the first stage high pressure turbine rotor blade of the F100-PW-220 engine, one of the most severely loaded components in the engine, is analyzed and a life assessment is performed. For this analysis, engine performance history is obtained from in-flight monitored engine parameters and flight conditions and downloaded for processing by a tool integrating a number of software tools and models. Data acquisition is performed by the FACE system installed in a large number of RNLAF F-16 fighter aircraft. Data then is processed by a thermodynamical engine system model, calculating gas properties like pressure and temperature at the required station in the engine. A computational fluid dynamics model, including the blade film cooling, is used to calculate the heat transfer to the blade. A thermal finite element model calculates the temperature distribution in the component and the stress distribution is obtained with a structural finite element analysis. Finally a life consumption model is used to determine the creep and fatigue damage accumulation in the component. The tool has significant potential to enhance on-condition maintenance and optimize aircraft operational use.
To support gas turbine operators, NLR is developing capabilities for life assessment of hot engin... more To support gas turbine operators, NLR is developing capabilities for life assessment of hot engine components. As a typical example the first rotor blades of the high pressure (HP) turbine of the F-100-PW-220 military turbofan will be discussed. For these blades tools have been developed to derive the blade temperature history from flight data obtained from F-16 missions. The resulting relative life consumption estimate should support the Royal Netherlands Air Force in their engine maintenance activities. The present paper describes the prediction method for the blade temperature, based on reverse engineering. Input data are the flight data of the engine performance parameters and the geometry of the HP turbine blades and vanes including film cooling orifices. The engine performance parameters are converted in HP turbine entry and exit conditions by the NLR Gas Turbine Simulation Program (GSP) engine model. Next a Computational Fluid dynamics (CFD) tool is used to calculate the resulting flow field and heat transfer coefficients without film cooling. An engineering method is used to predict the internal cooling and the resulting film injection temperature. The film cooling efficiency is estimated and a finite element method (FEM) for heat conduction completes the analysis tool. The method is illustrated by results obtained for the engine design point.
Analysis of combined convective and film cooling on an existing turbine blade W.B. de Wolf, S. Wo... more Analysis of combined convective and film cooling on an existing turbine blade W.B. de Wolf, S. Woldendorp and T. Tinga This report is based on a presentation held at the RTO-AVT Symposium on Heat Transfer
To support gas turbine operators, NLR is developing capabilities for life assessment of hot engin... more To support gas turbine operators, NLR is developing capabilities for life assessment of hot engine components. As a typical example the first rotor blades of the high pressure (HP) turbine of the FlOO- PW-220 military turbofan will be discussed. For these blades tools have been developed to derive the blade temperature history from flight data obtained from F-16 missions. The resulting relative life consumption estimate should support the Royal Netherlands Air Force in their engine maintenance activities. The present paper describes the prediction method for the blade temperature, based on reverse engineering. Input data are the flight data of the engine performance parameters and the geometry of the HP turbine blades and vanes including film cooling orifices. The engine performance parameters are converted in HP turbine entry and exit conditions by the NLR Gas Turbine Simulation Program (GSP) engine model. Next a Computational Fluid dynamics (CFD) tool is used to calculate the resu...
A method to predict gas turbine component life based on engine performance analysis is demonstrat... more A method to predict gas turbine component life based on engine performance analysis is demonstrated on a hot section gas turbine component. The mechanical and thermal loading of the first stage high pressure turbine rotor blade of the F100-PW-220 engine, one of the most severely loaded components in the engine, is analyzed and a life assessment is performed. For this analysis, engine performance history is obtained from in-flight monitored engine parameters and flight conditions and downloaded for processing by a tool integrating a number of software tools and models. Data acquisition is performed by the FACE system installed in a large number of RNLAF F-16 fighter aircraft. Data then is processed by a thermodynamical engine system model, calculating gas properties like pressure and temperature at the required station in the engine. A computational fluid dynamics model, including the blade film cooling, is used to calculate the heat transfer to the blade. A thermal finite element model calculates the temperature distribution in the component and the stress distribution is obtained with a structural finite element analysis. Finally a life consumption model is used to determine the creep and fatigue damage accumulation in the component. The tool has significant potential to enhance on-condition maintenance and optimize aircraft operational use.
To support gas turbine operators, NLR is developing capabilities for life assessment of hot engin... more To support gas turbine operators, NLR is developing capabilities for life assessment of hot engine components. As a typical example the first rotor blades of the high pressure (HP) turbine of the F-100-PW-220 military turbofan will be discussed. For these blades tools have been developed to derive the blade temperature history from flight data obtained from F-16 missions. The resulting relative life consumption estimate should support the Royal Netherlands Air Force in their engine maintenance activities. The present paper describes the prediction method for the blade temperature, based on reverse engineering. Input data are the flight data of the engine performance parameters and the geometry of the HP turbine blades and vanes including film cooling orifices. The engine performance parameters are converted in HP turbine entry and exit conditions by the NLR Gas Turbine Simulation Program (GSP) engine model. Next a Computational Fluid dynamics (CFD) tool is used to calculate the resulting flow field and heat transfer coefficients without film cooling. An engineering method is used to predict the internal cooling and the resulting film injection temperature. The film cooling efficiency is estimated and a finite element method (FEM) for heat conduction completes the analysis tool. The method is illustrated by results obtained for the engine design point.