A quick method for full flange-to-flange industrial gas turbine analysis based on through-flow modelling
Апстракт
In this paper flow field calculations for an entire two shaft industrial gas turbine will be described. This method is based on individual through flow codes for axial compressors and air-cooled expansion turbines developed by the authors which are automatically coupled using simple combustion and secondary flow models connecting compressor and turbine flow paths. With this approach the complete quasi 3-D flow field from compressor inlet to turbine exit can be solved simultaneously (flange-to-flange). Details are explained in this paper. The through-flow computation for the analysis of cooled axial multistage turbines is fed by air from the compressor bleeds which are part of the through flow model of the compressor. The through-flow methods are based on a stream function approach and a finite element solution procedure. They include high-fidelity loss and deviation models with improved correlations. Advanced radial mixing and endwall boundary layer models are applied to simulate 3-D f...low effects. For air-cooled turbine analysis, various types of cooling air injection were encompassed: film cooling, trailing edge injection and disc/endwall coolant flow. Compressor and turbine flow path computations were extensively validated individually and published by the authors. Predicted gas turbine operating points of MAN's MGT-gas turbine will be compared with results of the 3-D Navier- Stokes solver TBLOCK which was run for both compressor and turbines individually using the boundary conditions derived from the present analysis. The focus is on the comparison of mean data and radial distributions at inlet and outlet stations as well as planes between individual stages and blade rows. They will be compared with measured data at MAN's gas turbine test rig which were obtained in the turn of a prototype telemetry test campaign. It will be demonstrated that the new method presented is an essential and quick tool for overall gas turbine design and matching of the gas turbine components.
Извор:
International Journal of Gas Turbine, Propulsion and Power Systems, 2016, 8, 1, 9-18Издавач:
- Gas Turbine Society of Japan
Колекције
Институција/група
Mašinski fakultetTY - JOUR AU - Petrović, Milan AU - Abdel-Rahman, A. AU - Wiedermann, Alexander PY - 2016 UR - https://machinery.mas.bg.ac.rs/handle/123456789/2317 AB - In this paper flow field calculations for an entire two shaft industrial gas turbine will be described. This method is based on individual through flow codes for axial compressors and air-cooled expansion turbines developed by the authors which are automatically coupled using simple combustion and secondary flow models connecting compressor and turbine flow paths. With this approach the complete quasi 3-D flow field from compressor inlet to turbine exit can be solved simultaneously (flange-to-flange). Details are explained in this paper. The through-flow computation for the analysis of cooled axial multistage turbines is fed by air from the compressor bleeds which are part of the through flow model of the compressor. The through-flow methods are based on a stream function approach and a finite element solution procedure. They include high-fidelity loss and deviation models with improved correlations. Advanced radial mixing and endwall boundary layer models are applied to simulate 3-D flow effects. For air-cooled turbine analysis, various types of cooling air injection were encompassed: film cooling, trailing edge injection and disc/endwall coolant flow. Compressor and turbine flow path computations were extensively validated individually and published by the authors. Predicted gas turbine operating points of MAN's MGT-gas turbine will be compared with results of the 3-D Navier- Stokes solver TBLOCK which was run for both compressor and turbines individually using the boundary conditions derived from the present analysis. The focus is on the comparison of mean data and radial distributions at inlet and outlet stations as well as planes between individual stages and blade rows. They will be compared with measured data at MAN's gas turbine test rig which were obtained in the turn of a prototype telemetry test campaign. It will be demonstrated that the new method presented is an essential and quick tool for overall gas turbine design and matching of the gas turbine components. PB - Gas Turbine Society of Japan T2 - International Journal of Gas Turbine, Propulsion and Power Systems T1 - A quick method for full flange-to-flange industrial gas turbine analysis based on through-flow modelling EP - 18 IS - 1 SP - 9 VL - 8 UR - https://hdl.handle.net/21.15107/rcub_machinery_2317 ER -
@article{ author = "Petrović, Milan and Abdel-Rahman, A. and Wiedermann, Alexander", year = "2016", abstract = "In this paper flow field calculations for an entire two shaft industrial gas turbine will be described. This method is based on individual through flow codes for axial compressors and air-cooled expansion turbines developed by the authors which are automatically coupled using simple combustion and secondary flow models connecting compressor and turbine flow paths. With this approach the complete quasi 3-D flow field from compressor inlet to turbine exit can be solved simultaneously (flange-to-flange). Details are explained in this paper. The through-flow computation for the analysis of cooled axial multistage turbines is fed by air from the compressor bleeds which are part of the through flow model of the compressor. The through-flow methods are based on a stream function approach and a finite element solution procedure. They include high-fidelity loss and deviation models with improved correlations. Advanced radial mixing and endwall boundary layer models are applied to simulate 3-D flow effects. For air-cooled turbine analysis, various types of cooling air injection were encompassed: film cooling, trailing edge injection and disc/endwall coolant flow. Compressor and turbine flow path computations were extensively validated individually and published by the authors. Predicted gas turbine operating points of MAN's MGT-gas turbine will be compared with results of the 3-D Navier- Stokes solver TBLOCK which was run for both compressor and turbines individually using the boundary conditions derived from the present analysis. The focus is on the comparison of mean data and radial distributions at inlet and outlet stations as well as planes between individual stages and blade rows. They will be compared with measured data at MAN's gas turbine test rig which were obtained in the turn of a prototype telemetry test campaign. It will be demonstrated that the new method presented is an essential and quick tool for overall gas turbine design and matching of the gas turbine components.", publisher = "Gas Turbine Society of Japan", journal = "International Journal of Gas Turbine, Propulsion and Power Systems", title = "A quick method for full flange-to-flange industrial gas turbine analysis based on through-flow modelling", pages = "18-9", number = "1", volume = "8", url = "https://hdl.handle.net/21.15107/rcub_machinery_2317" }
Petrović, M., Abdel-Rahman, A.,& Wiedermann, A.. (2016). A quick method for full flange-to-flange industrial gas turbine analysis based on through-flow modelling. in International Journal of Gas Turbine, Propulsion and Power Systems Gas Turbine Society of Japan., 8(1), 9-18. https://hdl.handle.net/21.15107/rcub_machinery_2317
Petrović M, Abdel-Rahman A, Wiedermann A. A quick method for full flange-to-flange industrial gas turbine analysis based on through-flow modelling. in International Journal of Gas Turbine, Propulsion and Power Systems. 2016;8(1):9-18. https://hdl.handle.net/21.15107/rcub_machinery_2317 .
Petrović, Milan, Abdel-Rahman, A., Wiedermann, Alexander, "A quick method for full flange-to-flange industrial gas turbine analysis based on through-flow modelling" in International Journal of Gas Turbine, Propulsion and Power Systems, 8, no. 1 (2016):9-18, https://hdl.handle.net/21.15107/rcub_machinery_2317 .