CFD Aerodynamic Performance Validation of a Two-Stage High Pressure Turbine

Murari, Sridhar; Sunnam, Sathish; Goswami, Shraman; Liu, Jong S.

doi:10.1115/gt2011-45569

“…In addition, a mesh convergence study was carried out for HPT, which results in a Grid Convergence Index (Roache, 1993) of 0.0084 and the asymptotic character of the grid convergence was confirmed with 1.0058. Based on Sridhar (Sridhar et al, 2011), the Menter SST turbulence model (Menter, 1994) is applied for these simulations. The multimode model is used for transition, which is validated particularly for turbomachinery applications (Kožulovic, 2007).…”

Section: Cfd Methodsmentioning

confidence: 99%

Influence of combined compressor and turbine deterioration on the overall performance of a jet engine using RANS simulation and Pseudo Bond Graph approach

Goeing

¹

,

Seehausen

²

,

Pak

³

et al. 2020

J. Glob. Power Propuls. Soc.

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In this study, numerical models are used to analyse the influence of isolated component deterioration as well as the combination of miscellaneous deteriorated components on the transient performance of a high-bypass jet engine. For this purpose, the aerodynamic impact of major degradation effects in a high-pressure compressor (HPC) and turbine (HPT) is modelled and simulated by using 3D CFD (Computational Fluid Dynamics). The impact on overall jet engine performance is then modelled using an 1D Reduced Order Model (ROM). Initially, the HPC performance is investigated with a typical level of roughness on vanes and blades and the HPT performance with an increasing tip clearance. Subsequently, the overall performance of the jet engines with the isolated and combined deteriorated domains is computed by the in-house 1D performance tool ASTOR (AircraftEngine Simulation for Transient Operation Research). Degradations have a significant influence on the system stability and transient effects. In ASTOR, a system of differential equations including the equations of motion and further ordinary differential equations is solved. Compared to common ROMs, this enables a higher degree of accuracy. The results of temperature downstream of the high-pressure compressor and low-pressure turbine as well as the specific fuel composition and the HP rotational speed are used to estimate the degree and type of engine deterioration. However, the consideration of the system stability is necessary to analyse the characterisation in more detail. Finally, a simplified model which merges two engines with individual deteriorated domains into one combined deteriorated engine, is proposed. The simplified model predicts the performance of an engine which has been simulated with combined deteriorated components.

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“…In addition, a mesh convergence study was carried out for HPT, which results in a Grid Convergence Index (Roache, 1993) of 0.0084 and the asymptotic character of the grid convergence was confirmed with 1.0058. Based on Sridhar et al (Sridhar et al, 2011), the Menter SST turbulence model (Menter, 1994) is applied for these simulations. The multimode model is used for transition, which is validated particularly for turbomachinery applications (Kožulović, 2007).…”

Section: Cfd Methodsmentioning

confidence: 99%

Influence of combined compressor and turbine deterioration on the overall performance of a jet engine using RANS simulation and pseudo bond graph approach

Goeing¹,

Seehausen²,

Pak³

et al. 2020

Proceedings of Global Power &Amp; Propulsion Society

0

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In this study, numerical models are used to analyse the influence of isolated component deterioration as well as the combination of miscellaneous deteriorated components on the transient performance of a high-bypass jet engine. For this purpose, the aerodynamic impact of major degradation effects in a high-pressure compressor (HPC) and turbine (HPT) is modelled and simulated by using 3D CFD (Computational Fluid Dynamics). The impact on overall jet engine performance is then modelled using an 1D Reduced Order Model (ROM). Initially, the HPC performance is investigated with a typical level of roughness on vanes and blades and the HPT performance with an increasing tip clearance. Subsequently, the overall performance of the jet engines with the isolated and combined deteriorated domains is computed by the in-house 1D performance tool ASTOR (AircraftEngine Simulation for Transient Operation Research). Degradations have a significant influence on the system stability and transient effects. In ASTOR, a system of differential equations including the equations of motion and further ordinary differential equations is solved. Compared to common ROMs, this enables a higher degree of accuracy. The results of temperature downstream of the high-pressure compressor and low-pressure turbine as well as the specific fuel composition and the HP rotational speed are used to estimate the degree and type of engine deterioration. However, the consideration of the system stability is necessary to analyse the characterisation in more detail. Finally, a simplified model which merges two engines with individual deteriorated domains into one combined deteriorated engine, is proposed. The simplified model predicts the performance of an engine which has been simulated with combined deteriorated components. (CRC) 871 "Regeneration of Complex Capital Goods" which is funded by the Deutsche Forschungsgemeinschaft (DFG, German Research Foundation)-SFB 871/3-119193472. The authors would like to thank the DFG for the support. Moreover, the authors would like to acknowledge the substantial contribution of the DLR Institute of Propulsion Technology and MTU Aero Engines AG for providing TRACE.

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