Heat Transfer in Turbine Hub Cavities Adjacent to the Main Gas Path

Dixon, Jeffrey A.; Valencia, Antonio Guijarro; Bauknecht, Andreas; Coren, Daniel; Atkins, Nicholas R.

doi:10.1115/1.4006824

Cited by 9 publications

(6 citation statements)

References 5 publications

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“…A "perfect" matching was not possible for all thermocouples, as it was anticipated that the use of an automated coupling approach would be required to produce the best solution. This was reported in [5].…”

Section: Main Annulus Pressuresmentioning

confidence: 71%

“…These modelling capabilities have been validated using measured data from the two-stage turbine facility sited at the University of Sussex. Both steady and unsteady CFD solutions have been produced during the project, some presented at previous ASME conferences [5] and [6], with comparisons to measured data. Alternative cooling configurations have been both modelled and tested for a range of cooling flow levels.…”

Section: Cooling Airmentioning

confidence: 99%

“…thermal conductivity as a function of the metal temperature, are modelled. The 2D model being first used in the rig design phase, Dixon et al [5], to help establish operating temperatures, stress levels and clearances etc. and a full 3D sector model being created to support the validation of the coupled CFD/FE analysis.…”

Section: Finite Element Thermo-mechanical Modelsmentioning

confidence: 99%

“…The cavity meshing capability has been developed over the course of this five year research programme, e.g. from structured to unstructured meshes, with the usual checks on mesh sensitivity[5] [6].…”

mentioning

confidence: 99%

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Main Annulus Gas Path Interactions—Turbine Stator Well Heat Transfer

Dixon

Valencia

Coren

et al. 2013

Journal of Turbomachinery

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This paper summarizes the work of a five year research program 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 modeling methods of the cooling flow distribution and heat transfer management, in the environs of multistage turbine disk rims and blade fixings, with a view to maintaining component and subsystem integrity, while achieving optimum engine performance and minimizing 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) thermomechanical modeling codes. The main objective of the methodology is to help decide on optimum cooling configurations for disk temperature, stress, and life considerations. The new capability also gives us an effective means of validating the method by direct use of disk 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 optimization study has also been performed to support a redesign of the turbine stator well cavity to maximize the effectiveness of cooling air supplied to the disk 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 program. Comparisons will be provided of disk 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) and also the extension of the cavity cooling design optimization study to other new geometries.

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Section: Main Annulus Pressuresmentioning

confidence: 71%

Section: Cooling Airmentioning

confidence: 99%

Section: Finite Element Thermo-mechanical Modelsmentioning

confidence: 99%

mentioning

confidence: 99%

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Main Annulus Gas Path Interactions—Turbine Stator Well Heat Transfer

Dixon

Valencia

Coren

et al. 2013

Journal of Turbomachinery

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“…The amount of re-ingestion reduced with increasing sealing flow. This rig has also been extensively used to study heat transfer in turbine hub cavities e.g., Dixon et al [8].…”

Section: Gtp-15-1266 Scobiementioning

confidence: 99%

Design of an Improved Turbine Rim-Seal

Scobie

Teuber

et al. 2015

Journal of Engineering for Gas Turbines and Power

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Rim seals are fitted in gas turbines at the periphery of the wheel-space formed between rotor disks and their adjacent casings. These seals, also called platform overlap seals, reduce the ingress of hot gases which can limit the life of highly stressed components in the engine. This paper describes the development of a new, patented rim-seal concept showing improved performance relative to a reference engine design, using unsteady Reynolds-averaged Navier–Stokes (URANS) computations of a turbine stage at engine conditions. The computational fluid dynamics (CFD) study was limited to a small number of purge-flow rates due to computational time and cost, and the computations were validated experimentally at a lower rotational Reynolds number and in conditions under incompressible flow. The new rim seal features a stator-side angel wing and two buffer cavities between outer and inner seals: the angel-wing promotes a counter-rotating vortex to reduce the effect of the ingress on the stator; the two buffer cavities are shown to attenuate the circumferential pressure asymmetries of the fluid ingested from the mainstream annulus. Rotor disk pumping is exploited to reduce the sealing flow rate required to prevent ingress, with the rotor boundary layer also providing protective cooling. Measurements of gas concentration and swirl ratio, determined from static and total pressure, were used to assess the performance of the new seal concept relative to a benchmark generic seal. The radial variation of concentration through the seal was measured in the experiments and these data captured the improvements due to the intermediate buffer cavities predicted by the CFD. This successful design approach is a potent combination of insight provided by computation, and the flexibility and expedience provided by experiment.

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Computations on the flow characteristics and sealing performance of a stator well cavity for the second stage in gas turbine

Zhang

Wang

et al. 2017

Applied Thermal Engineering

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Heat Transfer in Turbine Hub Cavities Adjacent to the Main Gas Path

Cited by 9 publications

References 5 publications

Main Annulus Gas Path Interactions—Turbine Stator Well Heat Transfer

Main Annulus Gas Path Interactions—Turbine Stator Well Heat Transfer

Design of an Improved Turbine Rim-Seal

Computations on the flow characteristics and sealing performance of a stator well cavity for the second stage in gas turbine

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