Influence of Vane-Blade Spacing on Transonic Turbine Stage Aerodynamics: Part 1 — Time-Averaged Data and Analysis

Venable, B. L.; Delaney, R. A.; Busby, Judy; Davis, Roger L.; Dorney, Daniel J.; Dunn, Michael G.; Haldeman, Charles W.; Abhari, Reza S.

doi:10.1115/98-gt-481

Cited by 8 publications

(3 citation statements)

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“…A similar stator-rotor interaction study on a closely spaced profile was reported in Allegret-Bourdon, 29 where the presence of shock-waves in the flow-field showed a significant unsteadiness on the amplitude and the phase angle of the pressures values acting on the blade surface. This was also reported for this test case in the study by work Delaney et al 30 The above comparison serves to validate the solver capability in being able to predict the pressure distribution in relation to the experimental data. A fuller description of the flow field features was earlier reported in another report by this author.…”

Section: Test Casesupporting

confidence: 79%

Influence of fluid-structure interaction modelling on the stress and fatigue life evaluation of a gas turbine blade

Ubulom

2020

Proceedings of the Institution of Mechanical Engineers, Part A:

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A computational method of fluid-structure coupling is implemented to predict the fatigue response of a high-pressure turbine blade. Two coupling levels, herein referred to as a “fully coupled” and “decoupled” methods are implemented to investigate the influence of multi-physics interaction on the 3 D stress state and fatigue response of a turbine blade. In the fully-coupled approach, the solutions of the fluid-flow and the solid-domain finite element problem are obtained concurrently, while in the decoupled approach, the independently computed aerodynamic forces are unilaterally transferred as boundary conditions in the subsequent finite element solution. In both cases, a three-dimensional unsteady stator-rotor aerodynamic configuration is modelled to depict a forced-vibration loading of high-cycle failure mode. Also analyzed is the low-cycle phenomenon which arises due to the mean stresses of the rotational load of the rotating turbine wheel. The coupling between the fluid and solid domains (fully-coupled approach) provides a form of damping which reduces the amplitude of fluctuation of the stress history, as opposed to the decoupled case with a resultant higher amplitude stress fluctuation. While the stress amplitude is higher in the decoupled case, the fatigue life-limiting condition is found to be significantly influenced by the higher mean stresses in the fully-coupled method. The differences between the two approaches are further explained considering three key fatigue parameters; mean stress, multiaxiality stress state and the stress ratio factors. The study shows that the influence of the coupling between the fluid and structures domain is an important factor in estimating the fatigue stress history.

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Section: Test Casesupporting

confidence: 79%

Influence of fluid-structure interaction modelling on the stress and fatigue life evaluation of a gas turbine blade

Ubulom

2020

Proceedings of the Institution of Mechanical Engineers, Part A:

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“…The unsteady results indicate a very slight decrease in efficiency as the gap is reduced. These two-dimensional unsteady results are similar to those obtained by Venable et al [15]. The mixing-plane treatment, however, produces a very different trend.…”

Section: Effect Of Axial Gap On Turbine Stage Performancessupporting

confidence: 89%

“…However, the effect of axial gap between vane and rotor rows for turbines is less clear. There does not seem to be a consistent link between the gap distance and the stage aerodynamic performance, although a degradation in turbine efficiency at a smaller gap is often suspected [15]. The aerodynamic performances for the aforementioned turbine stage configuration were examined at different axial gaps.…”

Section: Effect Of Axial Gap On Turbine Stage Performancesmentioning

confidence: 99%

Three-dimensional unsteady Navier—Stokes analysis of stator—rotor interaction in axial-flow turbines

2000

Proceedings of the Institution of Mechanical Engineers, Part A:

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A three-dimensional full Navier-Stokes method is developed and applied to calculations of unsteady flows through multiple blade rows in axial-flow turbomachinery. The solver adopts the cellcentred finite volume discretization and the four-stage Runge-Kutta time-marching scheme. Unsteady calculations are effectively accelerated by using a time-consistent multi-grid technique, resulting in a speed-up by a factor of 10–20 with adequate temporal accuracy. The computational efficiency and validity of the present multi-grid technique are illustrated by comparisons with the results of the conventional dual time-stepping scheme. Calculated unsteady pressures on blade surfaces for a turbine stage performances at different stator-rotor axial gaps reveals a marked three-dimensional behaviour of the interaction between incoming wakes and rotor passage-vortex structures. The time-averaged losses from unsteady calculations show a noticeable spanwise redistribution compared with the steady results. Two dimensional and three-dimensional calculations indicate opposite trends in stage efficiency variation when the stator—rotor gap is reduced.

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Influence of Clocking and Vane/Blade Spacing on the Unsteady Surface Pressure Loading for a Modern Stage and One-Half Transonic Turbine

Haldeman

Krumanaker

Dunn

2003

Journal of Turbomachinery

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This paper describes pressure measurements obtained for a modern one and one-half stage turbine. As part of the experimental effort, the position of the high-pressure turbine (HPT) vane was clocked relative to the downstream low-pressure turbine (LPT) vane to determine the influence of vane clocking on both the steady and unsteady pressure loadings on the LPT vane and the HPT blade. In addition, the axial location of the HPT vane relative to the HPT blade was changed to investigate the combined influence of vane/blade spacing and clocking on the unsteady pressure loading. Time-averaged and time-accurate surface-pressure results are presented for several spanwise locations on the vanes and blade. Results were obtained at four different HPT vane-clocking positions and at two different vane/blade axial spacings for three (of the four) clocking positions. For time-averaged results, the effect of clocking is small on the HPT blade and vane. The influence of clocking on the transition ducts and the LPT vane is slightly greater (on the order of ±1%). Reduced HPT vane/blade spacing has a larger effect than clocking on the HPT vanes and blades ±3% depending upon the particular surface. Examining the data at blade passing and the first fundamental frequency, the effect of spacing does not produce a dramatic influence on the relative changes that occur between clocking positions. The results demonstrate that clocking and spacing effects on the surface pressure loading are very complex and may introduce problems if the results of measurements or analysis made at one span or location in the machine are extrapolated to other sections.

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Influence of Vane-Blade Spacing on Transonic Turbine Stage Aerodynamics: Part 1 — Time-Averaged Data and Analysis

Cited by 8 publications

References 0 publications

Influence of fluid-structure interaction modelling on the stress and fatigue life evaluation of a gas turbine blade

Influence of fluid-structure interaction modelling on the stress and fatigue life evaluation of a gas turbine blade

Three-dimensional unsteady Navier—Stokes analysis of stator—rotor interaction in axial-flow turbines

Influence of Clocking and Vane/Blade Spacing on the Unsteady Surface Pressure Loading for a Modern Stage and One-Half Transonic Turbine

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