Unsteady multistage analysis using a loosely coupled blade row approach

Dorney, Daniel J.; Davis, Roger L.; Sharma, Om P.

doi:10.2514/3.24024

Cited by 13 publications

(3 citation statements)

References 14 publications

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“…Generally, the flow field was not averaged in the tangential direction. This approach has some similarities to the one advocated by Dorney et al(1996) in their analysis of unsteady turbo-machinery flows. The approach used herein has the added simplification that the unsteadiness at the stator exit on the stator flow field was not considered.…”

Section: Introductionmentioning

confidence: 87%

Prediction of Nonuniform Inlet Temperature Effects on Vane and Rotor Heat Transfer

Boyle

Giel

1997

Volume 3: Heat Transfer; Electric Power; Industrial and Cogeneration

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The effects of nonuniform combustor exit temperature profiles on vane and rotor heat transfer were determined using a steady-state three-dimensional Navier-Stokes analysis. Both radial and tangential nonuniform temperature profiles were individually considered. Comparisons are made with experimental data for the effects of a radial temperature nonuniformity on rotor heat transfer. There was a decrease in stator heat load, and an increase in rotor heat load for a radial temperature distribution typically seen at the combustor exit. Tangential variations in stator inlet temperature produced significant variations in stator heat load, and resulted in average rotor heat load greater than for the uniform inlet temperature case. Rotor heat load was also calculated for different stator wake locations. Accounting for the stator wake position at the rotor inlet gave a greater average rotor heat load than that obtained by averaging the stator exit flow field in the tangential direction. The increase was most notable on the rotor pressure surface.

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Section: Introductionmentioning

confidence: 87%

Prediction of Nonuniform Inlet Temperature Effects on Vane and Rotor Heat Transfer

Boyle

Giel

1997

Volume 3: Heat Transfer; Electric Power; Industrial and Cogeneration

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“…In the other category, the incoming wakes are specified at the inlet of an isolated blade row. Dorney et al [222] proposed to solve the vane/blade interaction with a Loosely Coupled Blade Row (LCBR) approach, which belonged to the second category. The unsteady boundary conditions were periodically updated at the interfaces to include the unsteady effects coming from the upstream and the downstream rows.…”

Section: Loosely Coupled Approachmentioning

confidence: 99%

Unsteady Flows and Component Interaction in Turbomachinery

Salvadori,

Insinna,

Martelli

2024

IJTPP

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Unsteady component interaction represents a crucial topic in turbomachinery design and analysis. Combustor/turbine interaction is one of the most widely studied topics both using experimental and numerical methods due to the risk of failure of high-pressure turbine blades by unexpected deviation of hot flow trajectory and local heat transfer characteristics. Compressor/combustor interaction is also of interest since it has been demonstrated that, under certain conditions, a non-uniform flow field feeds the primary zone of the combustor where the high-pressure compressor blade passing frequency can be clearly individuated. At the integral scale, the relative motion between vanes and blades in compressor and turbine stages governs the aerothermal performance of the gas turbine, especially in the presence of shocks. At the inertial scale, high turbulence levels generated in the combustion chamber govern wall heat transfer in the high-pressure turbine stage, and wakes generated by low-pressure turbine vanes interact with separation bubbles at low-Reynolds conditions by suppressing them. The necessity to correctly analyze these phenomena obliges the scientific community, the industry, and public funding bodies to cooperate and continuously build new test rigs equipped with highly accurate instrumentation to account for real machine effects. In computational fluid dynamics, researchers developed fast and reliable methods to analyze unsteady blade-row interaction in the case of uneven blade count conditions as well as component interaction by using different closures for turbulence in each domain using high-performance computing. This research effort results in countless publications that contribute to unveiling the actual behavior of turbomachinery flow. However, the great number of publications also results in fragmented information that risks being useless in a practical situation. Therefore, it is useful to collect the most relevant outcomes and derive general conclusions that may help the design of next-gen turbomachines. In fact, the necessity to meet the emission limits defined by the Paris agreement in 2015 obliges the turbomachinery community to consider revolutionary cycles in which component interaction plays a crucial role. In the present paper, the authors try to summarize almost 40 years of experimental and numerical research in the component interaction field, aiming at both providing a comprehensive overview and defining the most relevant conclusions obtained in this demanding research field.

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“…With these approaches, more blade passing periods are needed before the periodic solution is attained and the extension to more than two blade rows seems complex and not yet fully documented. Some other approaches, such as the loosely coupled models, have been further developed [7,8] and a wider discussion can be found in reference [9]. Nevertheless, it is worth mentioning two further proposals that have been suggested more recently by Gerolymos et al [10] and Li and He [11].…”

Section: Introductionmentioning

confidence: 99%

Three-dimensional unsteady investigation of HP turbine stages

Adami

Martelli

2006

Proceedings of the Institution of Mechanical Engineers, Part A:

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This article deals with a three-dimensional unsteady numerical simulation of the unsteady rotor—stator interaction in a HP turbine stage. The numerical approach consists of a computational fluid dynamics (CFD) parallel code, based on an upwind total variation diminishing finite volume approach. The computation has been carried out using a sliding plane approach with hybrid unstructured meshes and a two-equation turbulent closure. The turbine rig under investigation is representative of the first stage of aeronautic gas turbine engines. A brief description of the cascade, the experimental setup, and the measuring technique is provided. Time accurate CFD computations of pressure fluctuations and Nusselt number are discussed against the experimental data.

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Unsteady multistage analysis using a loosely coupled blade row approach

Cited by 13 publications

References 14 publications

Prediction of Nonuniform Inlet Temperature Effects on Vane and Rotor Heat Transfer

Prediction of Nonuniform Inlet Temperature Effects on Vane and Rotor Heat Transfer

Unsteady Flows and Component Interaction in Turbomachinery

Three-dimensional unsteady investigation of HP turbine stages

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