Academic literature on the topic 'Combustor-turbine interaction'
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Journal articles on the topic "Combustor-turbine interaction"
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Flaszynski, Pawel, Michal Piotrowicz, and Tommaso Bacci. "Clocking and Potential Effects in Combustor–Turbine Stator Interactions." Aerospace 8, no. 10 (October 2, 2021): 285. http://dx.doi.org/10.3390/aerospace8100285.
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Investigations of combustors and turbines separately have been carried out for years by research institutes and aircraft engine companies, but there are still many questions about the interaction effect. In this paper, a prediction of a turbine stator’s potential effect on flow in a combustor and the clocking effect on temperature distribution in a nozzle guide vane are discussed. Numerical simulation results for the combustor simulator and the nozzle guide vane (NGV) of the first turbine stage are presented. The geometry and flow conditions were defined according to measurements carried out on a test section within the framework of the EU FACTOR (full aerothermal combustor–turbine interactions research) project. The numerical model was validated by a comparison of results against experimental data in the plane at a combustor outlet. Two turbulence models were employed: the Spalart–Allmaras and Explicit Algebraic Reynolds Stress models. It was shown that the NGV potential effect on flow distribution at the combustor–turbine interface located at 42.5% of the axial chord is weak. The clocking effect due to the azimuthal position of guide vanes downstream of the swirlers strongly affects the temperature and flow conditions in a stator cascade.
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Karki, K. C., V. L. Oechsle, and H. C. Mongia. "A Computational Procedure for Diffuser-Combustor Flow Interaction Analysis." Journal of Engineering for Gas Turbines and Power 114, no. 1 (January 1, 1992): 1–7. http://dx.doi.org/10.1115/1.2906301.
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This paper describes a diffuser-combustor flow interaction analysis procedure for gas turbine combustion systems. The method is based on the solution of the Navier–Stokes equations in a generalized nonorthogonal coordinate system. The turbulence effects are modeled via the standard two-equation (k-ε) model. The method has been applied to a practical gas turbine combustor-diffuser system that includes support struts and fuel nozzles. Results have been presented for a three-dimensional simulation, as well as for a simplified axisymmetric simulation. The flow exhibits significant three-dimensional behavior. The axisymmetric simulation is shown to predict the static pressure recovery and the total pressure losses reasonably well.
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Isvoranu, Dragos D., and Paul G. A. Cizmas. "Numerical Simulation of Combustion and Rotor-Stator Interaction in a Turbine Combustor." International Journal of Rotating Machinery 9, no. 5 (2003): 363–74. http://dx.doi.org/10.1155/s1023621x03000344.
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This article presents the development of a numerical algorithm for the computation of flow and combustion in a turbine combustor. The flow and combustion are modeled by the Reynolds-averaged Navier-Stokes equations coupled with the species-conservation equations. The chemistry model used herein is a two-step, global, finite-rate combustion model for methane and combustion gases. The governing equations are written in the strong conservation form and solved using a fully implicit, finite-difference approximation. The gas dynamics and chemistry equations are fully decoupled. A correction technique has been developed to enforce the conservation of mass fractions. The numerical algorithm developed herein has been used to investigate the flow and combustion in a one-stage turbine combustor.
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Muirhead, Kirsten, and Stephen Lynch. "Computational Study of Combustor Dilution Flow Interaction with Turbine Vanes." Journal of Propulsion and Power 35, no. 1 (January 2019): 54–71. http://dx.doi.org/10.2514/1.b36912.
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Cameron, C. D., J. Brouwer, C. P. Wood, and G. S. Samuelsen. "A Detailed Characterization of the Velocity and Thermal Fields in a Model Can Combustor With Wall Jet Injection." Journal of Engineering for Gas Turbines and Power 111, no. 1 (January 1, 1989): 31–35. http://dx.doi.org/10.1115/1.3240224.
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This work represents a first step in the establishment of a data base to study the interaction and influence of liquid fuel injection, wall jet interaction, and dome geometry on the fuel air mixing process in a flowfield representative of a practical combustor. In particular, the aerodynamic and thermal fields of a model gas turbine combustor are characterized via detailed spatial maps of velocity and temperature. Measurements are performed at an overall equivalence ratio of 0.3 with a petroleum JP-4 fuel. The results reveal that the flowfield characteristics are significantly altered in the presence of reaction. Strong on-axis backmixing in the dome region, present in the isothermal flow, is dissipated in the case of reaction. The thermal field exhibits the primary, secondary, and dilution zone progression of temperatures characteristic of practical gas turbine combustors. A parametric variation on atomizing air reveals a substantial sensitivity of the mixing in this flow to nozzle performance and spray symmetry.
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Farisco, Federica, Lukasz Panek, and Jim BW Kok. "Thermo-acoustic cross-talk between cans in a can-annular combustor." International Journal of Spray and Combustion Dynamics 9, no. 4 (July 2, 2017): 452–69. http://dx.doi.org/10.1177/1756827717716373.
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Thermo-acoustic instabilities in gas turbine engines are studied to avoid engine failure. Compared to the engines with annular combustors, the can-annular combustor design should be less vulnerable to acoustic burner-to-burner interaction, since the burners are acoustically coupled only by the turbine stator stage and the plenum. However, non-negligible cross-talk between neighboring cans has been observed in measurements in such machines. This study is focused on the analysis of the acoustic interaction between the cans. Simplified two-dimensional (2D) and three-dimensional (3D) equivalent systems representing the corresponding engine alike turbine design are investigated. Thermo-acoustic instabilities are reproduced using a forced response approach. Compressible large eddy simulation based on the open source computational fluid dynamics OpenFOAM framework is used applying accurate boundary conditions for the flow and the acoustics. A study of the reflection coefficient and of the transfer function between the cans has been performed. Comparisons between 2D and 3D equivalent configurations have been evaluated.
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Azwadi, Nor, and Ehsan Kianpour. "The Effect of Blowing Ratio on Film Cooling Effectiveness Using Cylindrical and Row Trenched Cooling Holes with Alignment Angle of 90 Degrees." Mathematical Problems in Engineering 2014 (2014): 1–9. http://dx.doi.org/10.1155/2014/470576.
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This paper presents the effects of blowing ratio on film cooling performance adjacent to the combustor endwall using cylindrical and row trenched cooling holes with alignment angle of 90 degrees. A three-dimensional representation of a Pratt and Whitney gas turbine engine was simulated and analysed using a commercial finite volume package FLUENT 6.2.26. The combustor simulator was designed to combine the interaction of two rows of dilution jets, which were staggered in the streamwise direction and aligned in the spanwise direction. As a result, the combustor with row trenched holes gave almost doubled cooling performance compared to the baseline case. In addition, the film cooling layer was increased at high blowing ratio, and thus it enhanced the cooling performance.
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Isvoranu, Dragos D., and Paul G. A. Cizmas. "Numerical Simulation of Combustion and Rotor-Stator Interaction in a Turbine Combustor." International Journal of Rotating Machinery 9, no. 5 (September 1, 2003): 363–74. http://dx.doi.org/10.1080/10236210309498.
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Stöhr, Michael, Isaac Boxx, Campbell D. Carter, and Wolfgang Meier. "Experimental study of vortex-flame interaction in a gas turbine model combustor." Combustion and Flame 159, no. 8 (August 2012): 2636–49. http://dx.doi.org/10.1016/j.combustflame.2012.03.020.
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Serbin, Sergey. "THERMO ACOUSTIC PROCESSES IN LOW EMISSION COMBUSTION CHAMBER OF GAS TURBINE ENGINE CAPACITY 25 MW." Science Journal Innovation Technologies Transfer, no. 2019-2 (May 5, 2019): 86–90. http://dx.doi.org/10.36381/iamsti.2.2019.86-90.
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The appliance of modern tools of the computational fluid dynamics for the investigation of the pulsation processes in the combustion chamber caused by the design features of flame tubes and aerodynamic interaction compressor, combustor and turbine is discussed. The aim of the research is to investigate and forecast the non-stationary processes in the gas turbine combustion chambers. The results of the numerical experiments which were carried out using three-dimensional mathematical models in gaseous fuels combustion chambers reflect sufficiently the physical and chemical processes of the unsteady combustion and can be recommended to optimize the geometrical and operational parameters of the low-emission combustion chamber. The appliance of such mathematical models are reasonable for the development of new samples of combustors which operate at the lean air-fuel mixture as well as for the modernization of the existing chambers with the aim to develop the constructive measures aimed at reducing the probability of the occurrence of the pulsation combustion modes. Keywords: gas turbine engine, combustor, turbulent combustion, pulsation combustion, numerical methods, mathematical simulation.
Dissertations / Theses on the topic "Combustor-turbine interaction"
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Legrenzi, Paolo. "A coupled CFD approach for combustor-turbine interaction." Thesis, Loughborough University, 2017. https://dspace.lboro.ac.uk/2134/26436.
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The current approach in the industry to numerically investigate the flow in a gas turbine considers each component, such as combustor and turbine, as a stand-alone part, involving no or very minor interactions with other parts, mainly applied through static boundary conditions. Efficient and very specialised CFD codes have been developed in the past to address the different flow characteristic occurring in the different regions of the engine. In order to meet the future requirements in terms of fuel consumption and pollutants emissions, an integrated approach capable of capturing all the possible interactions between different components is necessary. An efficient and accurate way to achieve integrated simulations is to couple already existing specialised codes in a zonal type of coupling. In this Thesis work a methodology to couple an incompressible/low-Mach number pressure-based combustion code with a compressible density-based turbomachinery code for industrial application has been developed. In particular two different couplings have been implemented: the first, based on the exchange of existing boundary conditions through files, comes as a completely separated tools from the original codes, of which no modifications are required, and it is applied to steady state simulations; the second instead, based on the exchange of boundary conditions and body forces through message passing, requires some modifications of the source codes and it is applied to both steady and unsteady cases. A simple analysis shows that not all the primitive variables can be made continuous at the coupling interface between the two codes and a compromise was found that allows minor discontinuity in some of the variables while achieving mass flow conservation and continuity of the temperature profiles. The coupling methodology has been applied to a simplified but realistic industrial case, consisting of a RQL (Rich Burn - Quick quench - Lean burn) combustor coupled with the first stage of the HP turbine. The analysis of the steady case has shown that the combustor field is affected as far as 150% axial chord lengths upstream of the blades leading edge, affecting RTDF and OTDF at the interfaces. In the turbine stage significant differences in both efficiency and degree of reaction were found in the coupled cases with respect to standard standalone simulations using radial inlet profiles. The analysis of the unsteady simulation has instead shown the hot streaks behaviour across the turbine, that are only partially mitigated by the stator blades and, due to segregation effect of hot and cold gases, migrate towards the pressure side of the rotor blades.
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Klapdor, Eva Verena [Verfasser], Johannes [Akademischer Betreuer] Janicka, and Heinz-Peter [Akademischer Betreuer] Schiffer. "Simulation of Combustor-Turbine Interaction in a Jet Engine / Eva Verena Klapdor. Betreuer: Johannes Janicka ; Heinz-Peter Schiffer." Darmstadt : Universitäts- und Landesbibliothek Darmstadt, 2011. http://d-nb.info/1105562603/34.
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Kao, Yi-Huan. "Experimental Investigation of Aerodynamics and Combustion Properties of a Multiple-Swirler Array." University of Cincinnati / OhioLINK, 2014. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1406881553.
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Greifenstein, Max [Verfasser], Andreas [Akademischer Betreuer] Dreizler, and Simone [Akademischer Betreuer] Hochgreb. "Experimental investigations of flame-cooling air interaction in an effusion cooled pressurized single sector model gas turbine combustor / Max Greifenstein ; Andreas Dreizler, Simone Hochgreb." Darmstadt : Universitäts- und Landesbibliothek, 2021. http://d-nb.info/1237816939/34.
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Stitzel, Sarah M. "Flow Field Computations of Combustor-Turbine Interactions in a Gas Turbine Engine." Thesis, Virginia Tech, 2001. http://hdl.handle.net/10919/30992.
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The current demands for higher performance in gas turbine engines can be reached by raising combustion temperatures to increase thermal efficiency. Hot combustion temperatures create a harsh environment which leads to the consideration of the durability of the combustor and turbine sections. Improvements in durability can be achieved through understanding the interactions between the combustor and turbine. The flow field at a combustor exit shows non-uniformities in pressure, temperature, and velocity in the pitch and radial directions. This inlet profile to the turbine can have a considerable effect on the development of the secondary flows through the vane passage.
This thesis presents a computational study of the flow field generated in a non-reacting gas turbine combustor and how that flow field convects through the downstream stator vane. Specifically, the effect that the combustor flow field had on the secondary flow pattern in the turbine was studied. Data from a modern gas turbine engine manufacturer was used to design a realistic, low speed, large scale combustor test section. This thesis presents the results of computational simulations done in parallel with experimental simulations of the combustor flow field.
In comparisons of computational predictions with experimental data, reasonable agreement of the mean flow and general trends were found for the case without dilution jets. The computational predictions of the combustor flow with dilution jets indicated that the turbulence models under-predicted jet mixing. The combustor exit profiles showed non-uniformities both radially and circumferentially, which were strongly dependent on dilution and cooling slot injection. The development of the secondary flow field in the turbine was highly dependent on the incoming total pressure profile. For a case with a uniform inlet pressure in the near-wall region no leading edge vortex was formed. The endwall heat transfer was found to also depend strongly on the secondary flow field, and therefore on the incoming pressure profile from the combustor.Master of Science
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Aslanidou, Ioanna. "Combustor and turbine aerothermal interactions in gas turbines with can combustors." Thesis, University of Oxford, 2015. https://ora.ox.ac.uk/objects/uuid:b1527fd0-8e54-4831-8625-32722141511e.
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As the research into the improvement of gas turbine performance progresses, the combustor-turbine interface becomes of increasing importance. In new engine designs components come closer together and the study of the combustor and turbine interactions can prove to be valuable for the improvement of the aerothermal performance of the vane. This thesis presents an experimental and numerical investigation of the aerodynamic and heat transfer aspect of the interactions between the combustor and the nozzle guide vane. In the gas turbine studied the trailing edge of the combustor transition duct wall is found upstream of every second vane. In the experimental measurements carried out in a purpose-built high speed experimental facility, the wake of this wall is shown to increase the aerodynamic loss of the vane. On the other hand, the wall alters secondary flow structures and has a protective effect on the heat transfer in the leading edge-endwall junction, a region that has proven to be detrimental to component life. The effect of different clocking positions of the vane relative to the combustor wall are tested experimentally and shown to alter the aerodynamic field and the heat transfer to the vane. The experimental methods and processing techniques adopted in this work are utilized to highlight the differences between the different cases studied. A new concept of using the combustor wall to shield the nozzle guide vane leading edge is introduced, followed by a proposed design that is numerically analysed, including a new cooling system. This uses continuous cooling slots on the upstream combustor wall to cool the vane leading edge. Coolant to the endwalls is provided from continuous slots on the combustor-turbine interface. The reduction of secondary flow through the removal of the horseshoe vortex in the new design results in improved cooling of the endwalls, with a higher average adiabatic effectiveness than in the original case, using the same coolant mass flow rate. The vane surface and suction side are also successfully cooled using less air than that required for a showerhead. The new vane is tested in the experimental facility. The improved aerodynamic and thermal performance of the shielded vane is demonstrated under engine-representative inlet conditions. The new design is shown to have a lower average total pressure loss than the original vane for all inlet conditions. The heat transfer on the vane surface is overall reduced for all inlet conditions and the peak heat transfer on the vane leading edge-endwall junction is moved further upstream, to a region that can be effectively cooled from the upstream cooling slots on the combustor wall trailing edge and the endwalls.
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Klapdor, Eva Verena. "Simulation of Combustor-Turbine Interaction in a Jet Engine." Phd thesis, 2011. https://tuprints.ulb.tu-darmstadt.de/2628/1/Dissertation_Klapdor.pdf.
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In the present work, “Simulation of Combustor-Turbine Interaction in a Jet Engine”, the theory and the simulation of combustor-turbine interaction in a jet engine are presented.
The objective of this thesis was the extension of a given incompressible CFD-code for the calculation of the compressible, reactive flow inside the combustor and the adjacent stator of a jet engine. The extended solver shall be used to investigate possible interaction between combustor and turbine of a jet engine.
The following two main topics were addressed:
The given incompressible solver PRECISE-UNSTRUCTURED, which is used by the combustor group of Rolls-Royce Deutschland, uses a SIMPLE procedure for the solution of the Navier-Stokes equations. This algorithm was extended with an all-Mach number formulation for the calculation of compressible flow. The implementation was verified and validated with several test cases. Comparison to analytical and experimental references showed good agreement. Simulations of a real first stator of a Rolls-Royce Deutschland jet engine were performed to demonstrate the ability of the code to calculate flow in complex geometries.
The combustion model PPDF-FGM (presumed probability density function-flamelet generated manifold) was to be used for the simulation of combustion. This model uses a stochastic mixture fraction and progress variable approach to account for chemistry-turbulence interaction. It was already available in the given code.
But the model was originally developed under the assumption of incompressible flow. Therefore, its coupling with the SIMPLE algorithm needed to be changed. A respective coupling mechanism was developed and implemented. The limiting cases, incompressible combustion and non-reactive compressible flow, were used to verify the implementation. The results using the coupled algorithm were as expected.
Finally, the developed code was used to perform an integrated simulation of a combustor and the first stator of a jet engine in one integral simulation. A second simulation without a stator was used to identify influences due to the stator on the flow in the rear part of the combustor.
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VAGNOLI, STEFANO. "Assessment of Advanced Numerical Methods for the Aero-Thermal Investigation of Combustor-Turbine Interactions." Doctoral thesis, 2016. http://hdl.handle.net/2158/1041923.
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The individual components of modern gas turbines are optimized to such a level that any noticeable improvement of the global performance can only be the result of a significant technological effort. In this sense, one of the main strategies to increase the efficiency of new generation engines lies in the investigation of more complex but more accurate design methodologies.
In particular, the different modules of a gas turbine are historically designed separately, despite the fact that a turbomachine is a fully integrated system where all components interact with each other.
In the turbomachinery community there is a growing interest in including the interfaces between different components into the design process, as it would enable to design compressors, combustors and turbines in an integrated manner by taking into account the real operating conditions of the machine.
The interface between combustion chamber and high pressure turbine is considered as the most critical one, as it directly affects the maximum temperature reached by the thermodynamic cycle. The flow field at the combustor-turbine interface is characterized by very high turbulence levels, swirl and temperature distortions, and the CFD methods currently used to design high pressure turbine (HPT) blades lack of validation for such an aggressive environment.
The aim of the present work is to develop new numerical methodologies and to analyze the accuracy of the existing ones when applied to multi-component simulations in turbomachinery. The attention is mainly focused on the interaction between combustor and turbine, as it represents the most critical interface for a modern gas turbines.
To take into account the mutual interaction between combustion chamber and HPT, in the first part of this thesis three CFD methodologies are developed to solve the flow field of the two components in an integrated framework. The procedures are validated on test cases of increasing complexity and successfully applied to a configuration representing a modern combustion chamber coupled to a nozzle guide vane.
In the second part, the advantages and limitations of RANS and LES applied to the study of the hot streak migration in HPTs are discussed. In this sense, a LES tool for the external aerodynamics of turbine blades is developed and validated, with the aim to be applied in the future to the investigation of the combustor-turbine interaction. The accuracy of LES is
then exploited to validate less time-consuming RANS models in predicting the hot streak migration in a turbine stage.
The current investigations indicate that integrated multi-component studiesare necessary to reproduce the actual operating conditions of the different components, as the complex interaction between hot streaks, swirl, turbulence and potential effect of the NGV cannot be reproduced without resolving the combustor and turbine at the same time. Moreover, the extreme
turbulence level at the combustor-turbine interface must be modeled with care, since it plays a major role in the migration and diffusion of the hot
streak in turbine.
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INSINNA, MASSIMILIANO. "Investigation of the Aero-Thermal Aspects of Combustor/Turbine Interaction in Gas Turbines." Doctoral thesis, 2015. http://hdl.handle.net/2158/986426.
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Taso, Jhy-Ming, and 曹志明. "Prediction on The Interaction of Swirl Flow and Jet In a Gas Turbine-Combustor." Thesis, 1995. http://ndltd.ncl.edu.tw/handle/58283033385393404423.
Full textBook chapters on the topic "Combustor-turbine interaction"
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Liu, Shi, and Hong Yin. "Research on the swirling flow effect of the combustor–turbine interaction on vane film cooling." In Advances in Materials Science, Energy Technology and Environmental Engineering, 145–56. P.O. Box 11320, 2301 EH Leiden, The Netherlands, e-mail: Pub.NL@taylorandfrancis.com , www.crcpress.com – www.taylorandfrancis.com: CRC Press/Balkema, 2016. http://dx.doi.org/10.1201/9781315227047-29.
Full textConference papers on the topic "Combustor-turbine interaction"
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Verma, Ishan, Laith Zori, Jaydeep Basani, and Samir Rida. "Modeling of Combustor and Turbine Vane Interaction." In ASME Turbo Expo 2019: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/gt2019-90325.
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Abstract Modern aero-engines are characterized by compact components (fan, compressor, combustor, and turbine). Such proximity creates a complex interaction between the components and poses a modeling challenge due to the difficulties in identifying a clear interface between components since they are usually modeled separately. From a numerical point of view, the simulation of a complex compact aero-engine system requires interaction between these individual components, especially the combustor-turbine interaction. The combustor is characterized by a subsonic chemically reacting and swirling flow while the high-pressure turbine (HPT) stage has flow which is transonic. Furthermore, the simulation of combustor-turbine interactions is more challenging due to aggressive flow conditions such as non-uniform temperature, non-uniform total-pressure, strong swirl, and high turbulence intensity. The simulation of aero-engines, where combustor-turbine interactions are important, requires a methodology that can be used in a real engine framework while ensuring numerical requirements of accuracy and stability. Conventionally, such a simulation is carried out using one of the two approaches: a combined simulation (or joint-simulation) of the combustor and the HPT geometries, or a co-simulation between the combustor and the turbine with the exchange of boundary conditions between these two separate domains. The primary objective of this paper is to assess the effectiveness of the joint simulation versus the co-simulation and propose a more practical approach for modeling combustor and turbine interactions. First, a detailed grid independence study with hexahedral and polyhedral meshes is performed to select the required polyhedral mesh. Then, an optimal location of the interface between the combustor and the nozzle guide vane (NGV) is identified. Co-simulations are then performed by exchanging information between the combustor and the NGV at the interface, wherein the combustor is solved using LES while the NGV is solved using RANS. The joint combustor-NGV simulations are solved using LES. The effect of the combustor-NGV interaction on the flow field and hot streak migration is analyzed. The results suggest that the joint simulation is computationally efficient and more accurate since both components are modelled together.
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Wolf, T., K. Lehmann, L. Willer, A. Pahs, M. Rößling, and L. Dorn. "InterTurb: High-Pressure Turbine Rig for the Investigation of Combustor-Turbine Interaction." In ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/gt2017-64153.
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This paper introduces a new 2-stage high-pressure turbine rig for aerodynamic investigations. It is operated by DLR Göttingen (Germany) and installed in DLR’s new testing facility NG-Turb. The rig’s geometrical size as well as the non-dimensional parameters are comparable to a modern engine in the small to medium thrust range. The turbine rig closely resembles engine hardware and features all relevant blade and vane cooling as well as secondary air-system flows. The effect of variations of each individual flow and different tip clearances on overall turbine efficiency will be studied. While the first part of the testing program will be based on uniform inlet conditions the second part will be run with a combustor simulator, which is based on electrical heaters and delivers a flow field similar to a rich-burn combustor. In order to find the optimum relative position for maximum turbine efficiency the combustor simulator can be rotated relative to the HPT inlet (clocking). For the same reasons the stators can also be clocked. The paper gives a brief overview of the testing facility and from there on focuses on the HPT rig features such as aerodynamic design, cooling and sealing flows. The aerodynamic optimisation of the stator vanes and shroudless rotor blades will be outlined. Further topics are the aerodynamic design of the combustor simulator, a comparison with engine combustors as well as the implementation in the rig. The paper also describes the rig instrumentation in the stationary and rotating system which most importantly focuses on measurements of efficiency and capturing of traverse data. The topic of blade and vane manufacturing via direct metal laser sintering will be briefly covered. The discussion of test results and comparison with numerical simulations will be the subject of a follow-up paper.
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Hilgert, Jonathan, Martin Bruschewski, Holger Werschnik, and Heinz-Peter Schiffer. "Numerical Studies on Combustor-Turbine Interaction at the Large Scale Turbine Rig (LSTR)." In ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/gt2017-64504.
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In order to fully understand the physical behavior of lean burn combustors and its influence on high pressure turbine stages in modern jet engines, the use of Computational Fluid Dynamics (CFD) promises to be a valuable addition to experimental techniques. The numerical investigations of this paper are based on the Large Scale Turbine Rig (LSTR) at Technische Universität Darmstadt, Germany which has been set up to explore the aerothermal combustor turbine interaction. The underlying numerical grids of the simulations take account of the complex cooling design to the fullest extent, considering coolant cavities, cooling holes and vane trailing edge slots within the meshing process. In addition to the k-ω-SST turbulence model, Scale-Adaptive Simulation (SAS) is applied for a computational domain comprising swirl generator and nozzle guide vanes in order to overcome the shortcomings of eddy viscosity turbulence models with regard to streamline curvature. The numerical results are compared with Five Hole Probe measurements at different streamwise locations showing good agreement and allowing for a more detailed examination of the complex flow physics caused by the interaction of turbine flow with lean-burn combustion and advanced film-cooling concepts. Moreover, numerically predicted Nu-contours on the hub end wall of the nozzle guide vane are validated by means of Infrared Thermography measurements.
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Klapdor, E. Verena, Stavros Pyliouras, Ruud L. G. M. Eggels, and Johannes Janicka. "Towards Investigation of Combustor Turbine Interaction in an Integrated Simulation." In ASME Turbo Expo 2010: Power for Land, Sea, and Air. ASMEDC, 2010. http://dx.doi.org/10.1115/gt2010-22933.
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Modelling combustor turbine interaction is to be performed in an integrated simulation of a combustion chamber and the nozzle guide vane of a jet engine. Starting with an incompressible pressure based combustion CFD code, two steps are required to obtain a code that is suitable for performing such calculations. Firstly, the SIMPLE algorithm needs to be extended to all-Mach-number flows. Secondly the solution algorithm needs to be modified to deal with combustion. This paper presents the first of these steps. A solver has been developed which is capable of computing both incompressible and transonic flows. Validation of modelling compressible viscous flow is performed using experimental data. The suitability of the algorithm to highly complex geometry is demonstrated on real engine nozzle guide vane geometry and results are compared to the results of other solvers.
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Notaristefano, Andrea, and Paolo Gaetani. "The Role of Turbine Operating Conditions on Combustor-Turbine Interaction – Part 2: Loading Effects." In ASME Turbo Expo 2022: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2022. http://dx.doi.org/10.1115/gt2022-82256.
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Abstract Aeroengine combustors burn a lean and premixed blend releasing vorticity and temperature perturbations. Interacting with the first turbine stage, these disturbances impact the cascade aerodynamics, add criticality to the blade cooling and are sources of noise. The first of these issues is addressed in this paper, focusing on off-design turbine conditions, as experienced by aero-engines in their duty. This paper, part II of a two-fold contribution, analyses the effect of the stage loading obtained by changing the RPM (three different values) at the same expansion ratio of 1.4, representative of subsonic flow conditions. Engine-representative disturbances are generated by a combustor simulator able to produce a swirling entropy wave. Two injection positions and four injection patterns are considered. Experimental measurements are carried out through the stage, measuring the injected disturbance and the aerothermal flow field downstream of the stator and the rotor. Results show that the swirl profile mostly impacts the stage aerodynamics. The different work extraction and the interaction with secondary flow structures change the entropy wave transport, diffusion and decay through the rotor. Furthermore, the increased angle of the incidence caused by the injected disturbance can make the blade stall under the most loaded operating condition.
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Muirhead, Kirsten, and Stephen P. Lynch. "A Computational Study of Combustor Dilution Flow Interaction with Turbine Vanes." In 55th AIAA Aerospace Sciences Meeting. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2017. http://dx.doi.org/10.2514/6.2017-0109.
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Verma, Ishan, Samir Rida, Laith Zori, Jaydeep Basani, Benjamin Kamrath, and Dustin Brandt. "Modeling of Combustor-Turbine Vane Interaction Using Stress-Blended Eddy Simulation." In ASME Turbo Expo 2021: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2021. http://dx.doi.org/10.1115/gt2021-59344.
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Abstract Modeling the interaction between gas turbine engine modules is complex. The compact nature of modern engines makes it difficult to identify an optimal interface location between components, especially in the hot section. The combustor and high-pressure turbine (HPT) are usually modeled separately with a one-way boundary condition transfer to the turbine inlet. This approach is not ideal for capturing all the intricate flow details that travel between the combustor and the turbine and for tracking hot streak migration that determines turbine durability. Modeling combustor-turbine interaction requires a practical methodology that can be leveraged during the engine design process while ensuring accurate, fast, and robust CFD solutions. The objective of this paper is to assess the effectiveness of joint simulation versus co-simulation in modeling combustor and turbine interaction. Co-simulations are performed by exchanging information between the combustor and the turbine stator at the interface, wherein the combustor is solved using Stress-Blended Eddy Simulation (SBES) while the stator is solved using RANS. The joint combustor-stator simulations are solved using SBES. The benefits of using SBES versus LES are explored. The effect of the combustor-stator interaction on the flow field and hot streak migration is analyzed. The results suggest that the SBES model is more accurate than LES for heat transfer predictions because of the wall treatment and the joint simulation is computationally efficient and less prone to interpolation errors since both hot section components are modeled in a single domain.
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Lo Presti, Federico, Marwick Sembritzky, Benjamin Winhart, Pascal Post, Francesca di Mare, Alexander Wiedermann, Johannes Greving, and Robert Krewinkel. "Numerical Investigation of Unsteady Combustor Turbine Interaction For Flexible Power Generation." In ASME Turbo Expo 2021: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2021. http://dx.doi.org/10.1115/gt2021-59329.
Full textAbstract:
Abstract With the growing importance of regenerative power generation and especially of a hydrogen-based economy, the full potential of gas turbines of the smaller output class (< 10 MW) can be ideally exploited to provide peak coverage of the energy need whilst stabilising the electric grids in the mid- and low-voltage range. Such machines can be typically started in a relatively short time (similarly to aero engines) and are capable, at the same time, of delivering dispatchable power-on-demand. A safe, stable and profitable operation under highly unsteady conditions poses renewed challenges for an optimal thermal management (especially in the HP stages) as well as control and surveillance of the machines. The understanding and hence predictability of the propagation of the temperature inhomogeneities originating at the combustor outlet remains hence a primary objective of current research, as persistent distortion patterns could be adopted at the turbine exhaust as diagnostic indications of a malfunction of the combustor, for example. In the present study low-frequency disturbances introduced by a periodic load variation have been simulated and superimposed to the inhomogeneous, unsteady flow entering a 3-stage, high-pressure industrial gas turbine fed by a can-type combustion chamber comprising 6 silo-burners. The effects of the unsteadiness realized at the combustor exit have been investigated by means of Detached Eddy Simulations, whereby a density-based solution approach with detailed thermodynamics has been employed. The periodic disturbances at the turbine inlet have been obtained by means of an artificially generated, unsteady field, resulting from a two-dimensional snapshot of the flow field at the combustor exit. Also, a combustor failure has been mimicked by reducing (respectively increasing) the mean temperature in some of the turbine inlet regions corresponding to the outlet of two burners. The propagation and amplitude changes of temperature fluctuations have been analyzed in the frequency domain. Tracking of the temperature fluctuations’ maxima at the lowest frequencies revealed characteristic migration patterns indicating that the corresponding fluctuations persist with a non-negligible amplitude up to the last rows. A distinct footprint could also be observed at the same locations when a combustor failure was simulated, showing that, in principle, the early detection of combustor failures is indeed possible.
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Raynaud, Félix, Ruud L. G. M. Eggels, Max Staufer, Amsini Sadiki, and Johannes Janicka. "Towards Unsteady Simulation of Combustor-Turbine Interaction Using an Integrated Approach." In ASME Turbo Expo 2015: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/gt2015-42110.
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In this paper a CFD solver with the ability of dealing with both reacting and compressible flows is developed, so that an integrated simulation of the whole system “combustor and turbine” can be performed. To its validation, the combustor-turbine interaction in a jet engine consisting of a Rolls-Royce combustor together with the first high-pressure turbine stage NGV (Nozzle-Guide-Vane) is studied. The unstructured CFD solver follows a pressure-based approach, using a PISO algorithm (Pressure Implicit with Splitting of Operator) recently extended for compressible flows. In order to allow acoustic waves to leave the computational domain, nonreflecting boundary conditions based on the NSCBC method (Navier-Stokes Characteristic Boundary Conditions) have been implemented. The numerical methods have been coupled with the Flamelet Generated Manifold combustion model (FGM) extended for compressible flows. After successfully verifying the NSCBC implementation, various numerical results describing the combustor-turbine interactions of the jet engine are analyzed and discussed in terms of temperature and total pressure fields with and without NGV. It could be shown that the influence of the NGV on the combustor flow is relatively limited. Differences in the combustor flow field are mainly due to spatial and temporal averaging used for the simulation without NGV to calculate the pressure field at combustor outlet. These numerical results demonstrate the ability of the developed numerical model in its steady computation mode to well capture the evolving flow properties in both combustor and turbine components.
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Notaristefano, Andrea, and Paolo Gaetani. "The Role of Turbine Operating Conditions on Combustor-Turbine Interaction – Part 1: Change in Expansion Ratio." In ASME Turbo Expo 2022: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2022. http://dx.doi.org/10.1115/gt2022-81707.
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Abstract Aeroengine lean-burn combustors release vorticity and temperature perturbations that, interacting with the first turbine stage, impact the stage aerodynamics, the blade cooling and noise production. The first of these issues is addressed in this paper that is part 1 of a two-fold contribution. A detailed experimental analysis is carried out to study the impact on the combustor-turbine interaction of the off-design conditions experienced by aero-engines in their duty. Engine-representative disturbances are generated by a combustor simulator able to produce swirling entropy waves. Two injection positions and four injection cases are studied. Experimental measurements are carried out at three traverses: upstream of the stator, at the interstage, and downstream of the rotor. This paper analyses the effect of the stage expansion ratio: two values are studied, namely 1.4 and 1.76, representative of subsonic and transonic flow conditions. They are chosen imposing similar velocity triangles at the rotor inlet. Results show that the swirl profile considerably impacts the stage aerodynamics. The aerothermal flow field downstream of the stator is modified significantly by the combustor disturbances. Conversely, downstream of the rotor, the differences in aerodynamics lessen. However, the entropy wave persists at the stage outlet and its transport depends on both the operating point and the injection position.