bluuebunny/crossref_metadata_2025_split huggingface dataset:
Uniform Crystal Temperature Sensor Accuracy Under Transient Conditions
Authors: DeVoe Jason , Odom Stephen , Ginzbursky Lev 
Published: August 2013

This paper investigates the accuracy of Uniform Crystal Temperature Sensors (UCTS) under transient conditions and describes a methodology for addressing sources of systematic error based on the findings. The study applies to the important task of thermal mapping of critical turbine parts during the engine development phase, for which UCTS is particularly well suited [1, 2, 3, 4]. A previous study focused on UCTS in steady state regimes and provided recommendations for optimizing the technique [5]. However, a substantial reduction in engine development costs may be achieved by being able to combine, for instance cyclic endurance tests with thermal mapping assuming that neither task will jeopardize the other.
The basic trends and magnitude of measurement errors were assessed as a function of factors such as UCTS installation configuration, thermo-physical properties of the installation materials and cycle characteristics. The authors used Finite Element Analysis to simulate transient heat transfer through a thin wall with an embedded UCTS. Stress calculations performed for the case of densely packed multi-UCTS installation on turbine blades showed no detrimental influence of standard micro-cavities on blade structural characteristics. These results were confirmed by a number of successful endurance tests, proving its compatibility with the task of thermography. Attention was focused on the cyclic test influence on the accuracy of thermal mapping. Single and multiple cycle test configurations have been considered.
After completion of a computational matrix, the characteristic results of interest are presented in the form of plots and diagrams to support the technical discussion. Recommendations drawn from this research will help analytical designers, test and instrumentation engineers to plan and execute dual task transient tests with a high accuracy of thermal mapping result interpretation.
First Results of a New Test Rig for the Research on the Internal Air System of an Industrial Gas Turbine
Authors: Günther André , Uffrecht Wieland , Odenbach Stefan , Caspary Volker 
Published: August 2013

Improvement of the internal air system has great impact on the efficiency and power of gas turbines. This paper describes a new two-stage test rig for research on the cooling air supply of industrial gas turbines. The design is modeled on a simplified geometry of the internal cavities of the high pressure turbine with receiver holes simulating the restriction imposed by internal blade cooling flow circuits. The test rig consists of a rotor-stator cavity and a full rotating cavity. The Stage One supply and the Stage Two supply are separated inside the rotorstator cavity. The intended aim of the research is the branched cooling air supply. The rim seal flow, which effect on cavity flows is known to be non-trivial, is outside the scope of this area of interest.
This paper concentrates on the flow path supplying the Stage Two. Variations of the axial gap size and the radial location of the connecting holes respectively the outlets of the rotor-stator cavity are described here. The air enters axially without pre-swirl at the outer radius of the stator and leaves the rotor-stator cavity through three rotating, axially directed connecting holes at a radius depending on the investigated case, which causes axial throughflow in Case 1 and radial inflow in Case 2.
The experimental results show that the net cavity mass flow, presented in terms of a reduced mass flow parameter, increases with increasing pressure ratio, rotational Reynolds number and gap size. The increase due to a larger gap size depends on the rotation and is less prominent at higher rotational Reynolds numbers. An axial throughflow at the outer radius results in higher values of the reduced mass flow parameter, as compared to the case with radial inflow. The difference between the two cases increases with increasing rotational Reynolds number. Measured static pressure fluctuations inside the rotor-stator cavity due to the rotating nozzles can be raised up to ± 4% of the mean in the case with the small gap and the outlet at outer radius. The Pitot probe measurements show a low swirl ratio, radial outflow near the rotor and radial inflow close to the stator, which is consistent with Batchelor-type flow.
Pre-Swirl Cooling Air Delivery System Performance Study
Authors: Didenko Roman A. , Karelin Dmitry V. , Ievlev Dmitry G. , Shmotin Yuri N. , Nagoga Georgy P. 
Published: August 2013

This paper reports the results from numerical simulations of the turbine blade cooling air delivery system performance using commercial CFD code Ansys CFX v11. Computations have been performed with variation of pre-swirl nozzle location radius, rotor-rotor rotating cavity width and the way of air transmission through the cover-plate. There are two ways of air transmission depending on the cover-plate design: through the CAO (circular array of orifices) or CAS (continuous annular slot). Computations are performed within the parameter range similar to gas-turbine engine operating conditions: 0.375<λT<0.98; 0.548<β0<2.5; 1.69·107<Reφ<2.33·107; 2.79·105<Cw<5.73·105.
It has been shown that the selection of optimum radius of pre-swirl nozzle location is determined by different factors and depends on design and boundary conditions. The rotor-rotor rotating cavity width does not affect delivery system performances and is selected by a designer based on the constructional necessity, strength, weight and dynamic behavior of the turbine rotor. Rotating orifices reduce the swirl ratio βb before the blade cooling rim slot reduce adiabatic effectiveness Θ and increase loss coefficient ζ.
Numerical and Experimental Investigation of Secondary Flows and Influence of Air System Design on Heavy-Duty Gas Turbine Performance
Authors: Bozzi Luca , D’angelo Enrico 
Published: August 2013

High turn-down operating of heavy-duty gas turbines in modern Combined Cycle Plants requires a highly efficient secondary air system to ensure the proper supply of cooling and sealing air. Thus, accurate performance prediction of secondary flows in the complete range of operating conditions is crucial.
The paper gives an overview of the secondary air system of Ansaldo F-class AEx4.3A gas turbines. Focus of the work is a procedure to calculate the cooling flows, which allows investigating both the interaction between cooled rows and additional secondary flows (sealing and leakage air) and the influence on gas turbine performance. The procedure is based on a fluid-network solver modelling the engine secondary air system. Parametric curves implemented into the network model give the consumption of cooling air of blades and vanes. Performances of blade cooling systems based on different cooling technology are presented. Variations of secondary air flows in function of load and/or ambient conditions are discussed and justified.
The effect of secondary air reduction is investigated in details showing the relationship between the position, along the gas path, of the upgrade and the increasing of engine performance. In particular, a section of the paper describes the application of a consistent and straightforward technique, based on an exergy analysis, to estimate the effect of major modifications to the air system on overall engine performance. A set of models for the different factors of cooling loss is presented and sample calculations are used to illustrate the splitting and magnitude of losses. Field data, referred to AE64.3A gas turbine, are used to calibrate the correlation method and to enhance the structure of the lumped-parameters network models.
Multi-Row Film Cooling Performances of a High Lift Blade and Vane
Authors: Naik S. , Krueckels J. , Gritsch M. , Schnieder M. 
Published: August 2013

This paper investigates the aerodynamic and film cooling effectiveness characteristics of a first stage turbine high lift guide vane and its corresponding downstream blade. The vane and blade geometrical profiles and operating conditions are representative of that normally found in a heavy-duty gas turbine. Both the vane and the blade airfoils consist of multi-row film cooling holes located at various axial positions along the airfoil chord. The film cooling holes are geometrically three-dimensional in shape and depending on the location on the airfoil; they can be either symmetrically fan shaped or non-symmetrically fan shaped. Additionally the film cooling holes can be either compounded or in-line with the external flow direction.
Numerical studies and experimental investigations in a linear cascade have been conducted at vane and blade exit isentropic Mach number of 0.8. The influence of the coolant flow ejected from the film cooling holes has been investigated for both the vane and the blade profiles.
For the nozzle guide vane, the measured film cooling effectiveness compared well with the predictions, especially on the pressure side. The suction side film cooling effectiveness, which consisted of two pre-throat film rows, proved very effective up-to the suction side trailing edge. For the blade, there was a reasonable comparison between the measured and predicted film cooling effectiveness. Again the blade pre-throat fan shaped cooling holes proved very effective up-to the suction side trailing edge. For the vane, the impact of varying the blowing ratios showed a strong variation in the film cooling effectiveness on the pressure side. However, on the blade, the effect of varying the blowing ratio had a greater impact on the suction side film effectiveness compared to the pressure side.
Experimental Measurements of Ingestion Through Turbine Rim Seals: Part 3—Single and Double Seals
Authors: Sangan Carl M. , Scobie James A. , Owen J. Michael , Pountney Oliver J. , Wilson Mike , Lock Gary D. 
Published: August 2013

This paper describes experimental results from a research facility which experimentally models hot gas ingress into the wheel-space of an axial turbine stage. Measurements of CO2 gas concentration in the rim-seal region and inside the wheel-space are used to assess the performance of generic (though engine-representative) single and double seals in terms of the variation of concentration effectiveness with sealing flow rate. The variation of pressure in the turbine annulus, which governs externally-induced ingress, was obtained from steady pressure measurements downstream of the vanes.
The benefit of using double seals is demonstrated: the ingested gas is shown to be predominately confined to the outer wheel-space radially outward of the inner seal; in the inner wheel-space, radially inward of the inner seal, the effectiveness is shown to be significantly higher. Criteria for ranking the performance of single and double seals are proposed, and the performance limit for any double seal is shown to be one in which the inner seal is exposed to rotationally-induced ingress.
Although the ingress is a consequence of an unsteady, three-dimensional flow field and the cause-effect relationship between pressure and the sealing effectiveness is complex, the experimental data is shown to be successfully calculated by simple effectiveness equations developed from a theoretical model. The data illustrate that, for similar turbine-stage velocity triangles, the effectiveness can be correlated using two empirical parameters. In principle, these correlations could be extrapolated to a geometrically-similar turbine operating at engine-representative conditions.
Passive Effusion Cooling in a Rectangular S-Bend Diffuser
Authors: Ng B. C. N. , Birk A. M. 
Published: August 2013

The experimental study considered passive effusion cooling in an S-bend diffusing passage in which ambient cool air was drawn naturally into the S-duct passage with sub-atmospheric flow distributions.
Seven-hole pressure probes were used to measure the test section’s inlet and outlet flow conditions that were used to evaluate the performance of the S-bend diffuser. Back-pressure, outlet flow-fields and wall pressure distributions were investigated to study the effects of effusion cooling on the pressure recovery performance of the S-bend diffuser.
The study revealed a substantial back-pressure penalty and wall pressure distribution alteration in the S-bend passage with full coverage effusion cooling. The outlet diffuser was shown to be not as effective with effusion cooling. The findings highlighted the importance of the design of effusion holes locations in complex flow passages.
Main Annulus Gas Path Interactions: Turbine Stator Well Heat Transfer
Authors: Dixon Jeffrey A. , Valencia Antonio Guijarro , Coren Daniel , Eastwood Daniel , Long Christopher 
Published: August 2013

This paper summarises the work of a 5-year research programme into the heat transfer within cavities adjacent to the main annulus of a gas turbine. The work has been a collaboration between several gas turbine manufacturers, also involving a number of universities working together. The principal objective of the study has been to develop and validate computer modelling methods of the cooling flow distribution and heat transfer management, in the environs of multi-stage turbine disc rims and blade fixings, with a view to maintaining component and sub-system integrity, whilst achieving optimum engine performance and minimising emissions.
A fully coupled analysis capability has been developed using combinations of commercially available and in-house computational fluid dynamics (CFD) and finite element (FE) thermo-mechanical modelling codes. The main objective of the methodology is to help decide on optimum cooling configurations for disc temperature, stress and life considerations. The new capability also gives us an effective means of validating the method by direct use of disc temperature measurements, where otherwise, additional and difficult to obtain parameters, such as reliable heat flux measurements, would be considered necessary for validation of the use of CFD for convective heat transfer.
A two-stage turbine test rig has been developed and improved to provide good quality thermal boundary condition data with which to validate the analysis methods. A cooling flow optimisation study has also been performed to support a re-design of the turbine stator well cavity, to maximise the effectiveness of cooling air supplied to the disc rim region. The benefits of this design change have also been demonstrated on the rig. A brief description of the test rig facility will be provided together with some insights into the successful completion of the test programme. Comparisons will be provided of disc rim cooling performance, for a range of cooling flows and geometry configurations.
The new elements of this work are the presentation of additional test data and validation of the automatically coupled analysis method applied to a partially cooled stator well cavity, (i.e. including some local gas ingestion); also the extension of the cavity cooling design optimisation study to other new geometries.
Use of Dynamic Meshes for Transient Metal Temperature Prediction
Authors: Amirante Dario , Hills Nicholas J. , Barnes Christopher J. 
Published: August 2013

This paper describes the thermal analysis conducted on a three-dimensional model of a stator well contained within a turbine assembly. A methodology has been developed for coupled fluid-solid modelling accounting for the boundary deflections predicted by the structural analysis. The coupling is obtained through an iterative process between a finite element code (FEA) performing structural and thermal analysis for the solid part, and a finite volume solver for the CFD. As the engine runs transiently through a specified flight cycle, the FEA predictions of metal deformations and temperatures are passed to the CFD code, which in turns computes the heat fluxes over the metal surfaces. A robust moving mesh technique is used to automatically modify an initial mesh, based on the cold geometry, to the time dependent boundary deflections. Thus, the methodology guarantees that the CFD is always carried out on the hot-running geometry.
A thorough investigation into the flow physics involved in the stator well is conducted. It is shown that an accurate thermal modelling for transient regimes necessitates the correct prediction of the time dependent clearances present in the system. Even small changes in the clearances may cause a transition between different dynamic behaviours, egress or ingestion, ultimately leading to drastically different thermal responses.
Simple Particle Separator for the Secondary Air System of Gas Turbines
Authors: Víllora Natalia García , Dullenkopf Klaus , Bauer Hans-Jörg , Bricaud Cyrille , Zierer Thomas 
Published: August 2013

In heavy-duty gas turbines as well as in aero-engines, air is extracted from the compressor and led to the hot parts of the combustor and the turbine in order to cool them. Despite active design solutions such as material selection, and inclusion of compressor inlet filters, dust holes, and so on, the cooling air can be charged with solid particles, which can block the cooling holes. Therefore prediction of the particle behaviour within the secondary air system remains crucial for the design of a robust and efficient cooling system for the hot parts.
For this study a particle separator prototype was designed by Alstom and its particle separation efficiency together with its total pressure losses were measured at the Institute of Thermal Turbomachinery (ITS) at the Karlsruher Institute of Technology (KIT) for two geometrical configurations and numerous flow conditions. The test rig design was optimized to provide accurate boundary conditions for the simulations. In addition, the influence of the particle shape, size, and density on the separation efficiency was studied.
The experimental results were used to validate the predicted flow field and to evaluate standard methods available in a commercial CFD-solver, to simulate the interaction of solid particles with turbulent flows and the containing walls. Comparisons between the measured and calculated separation efficiencies were performed for spherical and flat particles with different Stokes numbers. In particular, the way in which a simple modelling approach used for the prediction of sphere trajectories can be transferred to flat particles was investigated. Finally this study delivers generic data for improved modelling of solid particles, like spheres and flat particles, in turbulent flows.
Numerical Validation of Heat Transfer Characteristics for Shower Head Film Cooled Turbine Vane
Authors: Vishnumolakala Reddaiah , Liu Jong S. , Murari Sridhar , Bommisetty Ramakumar 
Published: August 2013

In modern gas turbines, film cooling is one of the widely used external cooling techniques for turbine vanes and blades. The turbine airfoil leading edge, which is highly loaded thermally, is currently protected from the hot gas by film cooling schemes, so called showerhead cooling. Flow field in film cooling is very complex and detailed knowledge of heat transfer rates and metal temperatures are required while designing these cooling systems.
Computational Fluid Dynamics (CFD) is gaining popularity for modeling these complex cooling systems. However, the application of CFD depends on its accuracy and reliability. This requires the CFD code to be validated with laboratory measurements to ensure its predictive capacity. In this regard, a project has been taken to validate the commercially available CFD code for predicting the blade heat transfer characteristics with shower head film cooling.
The validation is accomplished with the test results of Ames [5]. C3X vanes were used for their four vane cascade test facility. The showerhead array used consists of 5 rows of 20° spanwise slanted holes. Experiments were carried out with lower (1%) and higher (12%) turbulence intensities. Results of metal temperatures and heat transfer coefficients were reported.
The objective of this study is to validate and calibrate a commercially available CFD code, against the available test data [5] and to understand the relationship between complex flow fields and heat transfer behavior. STAR-CCM+ is used for model generation, mesh generation and solution. Polyhedral elements with prism layers around the wall surfaces are generated. Three turbulence models, Durbin’s v2f model, Menter SST and SST transition models are explored in this study. Simulations are performed for two turbulence intensities available. Typical flow parameters such as blade surface heat transfer coefficient (HTC), surface temperatures and the location of flow transition are compared. Results were compared for two typical cascade exit Mach number conditions such as 0.2 and 0.7, which represents subsonic and transonic conditions respectively.
Except in suction side transition region, numerically simulated heat transfer coefficient and Stanton number matched well with test data. Vane wall temperature contours were presented to understand the heat transfer behavior. The heat transfer behavior was numerically investigated for realistic exit Mach numbers. Sensitivity study for two inlet free stream turbulence intensities and three inlet free stream turbulence length scales are performed for realistic exit Mach number and reported heat transfer coefficient and Stanton number.
Effect of the Biot Number on Metal Temperature of Thermal-Barrier-Coated Turbine Parts: Real Engine Measurements
Authors: Henze Marc , Bogdanic Laura , Muehlbauer Kurt , Schnieder Martin 
Published: August 2013

For numerous hot gas parts (e.g. blades or vanes) of a gas turbine, thermal barrier coating (TBC) is used to reduce the metal temperature to a limit that is acceptable for the component and the required lifetime. However, the ability of the TBC to reduce the metal temperature is not constant, it is a function of Biot and Reynolds number. This behavior might lead to a vane’s or blade’s metal temperature increase at lower load relative to a reference load condition of the gas turbine (i.e. at lower operating Reynolds number).
A measurement campaign has been performed, to evaluate metal temperature measurements on uncoated and coated turbine parts in Alstom’s GT26 test power plant in Switzerland. Herewith the impact of varying Reynolds number on the ability of the TBC to protect the turbine components was evaluated.
This paper reports on engine-run validation, including details on the application of temperature sensors on thermal-barrier-coated parts. Different methods for the application of thermocouples that were taken into account during the development of the application process are shown.
Measurement results for a range of Reynolds number are given and compared to model predictions. Focus of the evaluation is on the measurements underneath the TBC. The impact of different Reynolds number on the ability of the TBC to protect the parts against the hot gas is shown. TBC coated components show under certain circumstances higher metal temperatures at lower load compared to a reference load condition. The measurement values obtained from real engine tests can be confirmed by 1D-model predictions that explain the dependency of the TBC effect on Biot and Reynolds number.