The Interaction of Turbine Inter-Platform Leakage Flow With the Mainstream Flow

Reid, Kevin; Denton, J. D.; Pullan, Graham; Curtis, Eric; Longley, John P.

doi:10.1115/gt2005-68151

Cited by 13 publications

(12 citation statements)

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“…The lower expansion ratio also results in a 4.8% reduction in power output and torque. The flow behaviour observed and the changes in the turbine performance parameters are in line with the results presented by Blanco et al (2) , Reid et al (4) and Palmer et al (8) .…”

Section: Comparison Of Clean and Un-displaced Rotor Configurationsupporting

confidence: 90%

“…Popovic et al (3) described the flow structure of the leakage from rim seals and suggested methodologies to approach the rim seal design for better sealing from hot air ingestion and lower losses. Reid et al (4) developed a relation between the leakage flow rates and rotor pressure losses in an intermediate-pressure turbine stage. Paniagua et al (5) carried out an experimental and computational study of the impact of leakage flows in a transonic High-Pressure (HP) turbine.…”

Section: Introductionmentioning

confidence: 99%

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Aerodynamic performance of an un-located high-pressure turbine rotor

2017

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The rotor sub-assembly of the high-pressure turbine of a modern turbofan engine is typically free to move downstream because of the force imbalance acting on the disc and blades following an un-located shaft failure. This downstream movement results in a change in the geometry of the rotor blade, tip seals and rim/platform seals because of the interaction of the rotor sub-assembly with the downstream vane sub-assembly. Additionally, there is a change in the leakage flow properties, which mix with the main flow because of the change in engine behaviour and secondary air system dynamics. In the present work, the changes in geometry following the downstream movement of the turbine, are obtained from a validated friction model and structural LS-DYNA simulations. Changes in leakage flow properties are obtained from a transient network source-sink secondary air system model. Three-dimensional Reynolds-averaged Navier-Stokes simulations are used to evaluate the aerodynamic effect from the inclusion of the leakage flows, tipseal domains, and downstream movement of the rotor for three displacement configurations (i.e. 0, 10 and 15 mm) with appropriate changes in geometry and leakage flow conditions. It is observed from the results that there is a significant reduction in the expansion ratio, torque and power produced by the turbine with the downstream movement of the rotor because of changes in the flow behaviour for the different configurations. These changes in turbine performance parameters are necessary to accurately predict the terminal speed of the rotor using an engine thermodynamic model. Further, it is to be noted that such reductions in turbine rotor torque will result in a reduction of the terminal speed attained by the rotor during an un-located shaft failure. Therefore the terminal speed of the rotor can be controlled by introducing design features that will result in the rapid rearward displacement of the turbine rotor.

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Section: Comparison Of Clean and Un-displaced Rotor Configurationsupporting

confidence: 90%

Section: Introductionmentioning

confidence: 99%

Aerodynamic performance of an un-located high-pressure turbine rotor

2017

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“…Another turbine leakage feature known to contribute significantly to aerodynamic loss is the inter-platform gap between airfoil segments in a wheel. Reid, et al [9] found that turbine efficiency was decreased significantly by the presence of a platform gap in the endwall, but efficiency was not sensitive to platform gap leakage flowrate. A later study by Reid, et al [10] varied the location and angle of the platform gap and determined an improvement in stage efficiency for a gap located in a region of relatively constant static pressure.…”

Section: Relevant Past Studiesmentioning

confidence: 99%

Aerodynamic Loss for a Turbine Blade With Endwall Leakage Features and Contouring

Lynch

Thole

Kohli

et al. 2013

Volume 6A: Turbomachinery

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Secondary flows near the endwall of a turbine blade contribute to a loss in aerodynamic performance in the engine. Further reductions in performance occur when the secondary flows interact with leakage flow from necessary clearance features, such as the clearance gap between the blade rotor and an upstream stator or gaps between adjacent blade platforms. Non-axisymmetric endwall contouring has been shown to reduce the strength of secondary flows near the endwall, but relatively little research has been done to test the sensitivity of the contouring to the endwall leakage features. This paper describes aerodynamic measurements taken downstream of a cascade with representative leakage features. In general, upstream leakage flow with swirl relative to the blade increased aerodynamic loss, relative to leakage that was matched to the blade wheelspeed. Non-axisymmetric contouring for an endwall without a platform gap reduced underturning of the flow but had no effect on overall loss, relative to a flat endwall without a gap. A contoured endwall with a platform gap had 12% higher mixed-out loss than a contoured endwall without a gap.

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“…The TBLOCK solver is widely used in both industry and in academia, and is the latest in a long line of previous codes by Denton that are known collectively as the "Denton codes". A complete description of the algorithm used by the solver is given by Klostermeier [11] while shorter overviews and examples of its application to turbomachinery research have been published by Reid et al [12] and Rosic et al [13]. In addition, the motivation for the current method can be traced through a series of papers by Denton [14][15] [16].…”

Section: Application Case Studymentioning

confidence: 99%

SBLOCK: A Framework for Efficient Stencil-Based PDE Solvers on Multi-core Platforms

Brandvik

Pullan

2010

2010 10th IEEE International Conference on Computer and Information Technology

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We present a new software framework for the implementation of applications that use stencil computations on block-structured grids to solve partial differential equations. A key feature of the framework is the extensive use of automatic source code generation which is used to achieve high performance on a range of leading multi-core processors. Results are presented for a simple model stencil running on Intel and AMD CPUs as well as the NVIDIA GT200 GPU. The generality of the framework is demonstrated through the implementation of a complete application consisting of many different stencil computations, taken from the field of computational fluid dynamics.

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The Interaction of Turbine Inter-Platform Leakage Flow With the Mainstream Flow

Cited by 13 publications

References 0 publications

Aerodynamic performance of an un-located high-pressure turbine rotor

Aerodynamic performance of an un-located high-pressure turbine rotor

Aerodynamic Loss for a Turbine Blade With Endwall Leakage Features and Contouring

SBLOCK: A Framework for Efficient Stencil-Based PDE Solvers on Multi-core Platforms

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