The Influence of Combustor Swirl on Pressure Losses and the Propagation of Coolant Flows at the Large Scale Turbine Rig (LSTR): Experimental and Numerical Investigation

Werschnik, Holger; Schneider, Marius; Herrmann, Janina; Ivanov, Dimitri A.; Schiffer, Heinz-Peter; Lyko, Christoph

doi:10.3390/ijtpp2030012

Cited by 24 publications

(13 citation statements)

References 21 publications

(30 reference statements)

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“…However, previous experimental campaigns in a wind tunnel have shown that the wake is completely reabsorbed at stator leading edge [20]. As such, the aforementioned flow features of the generated swirl make the generated vortex comparable to what documented in literature [16,17,25,26].…”

Section: Generated Disturbancesupporting

confidence: 72%

Transport of Swirling Entropy Waves through an Axial Turbine Stator

Notaristefano

Gaetani

2021

IJTPP

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The transport of entropy waves and their impact on the stage aerodynamics are still open questions. This paper shows the results of an experimental campaign that focuses on the swirling entropy waves advection through an axial turbine stator. The research aims at quantifying the aerodynamic impact of the swirling entropy waves on the first nozzle and characterizing their transport. The disturbance is generated by a novel entropy wave generator that ensures a wide set of different injection parameters. The device injects the disturbance axially, four different clocking positions are investigated. Measurements show a severe temperature attenuation of the swirling entropy wave at stator outlet. The high temperature location changes with the injection position as a result of the different interaction with the stator secondary flows. Depending on the injection position, the aerodynamic flow field is strongly perturbed by the injected swirl profile, instead the entropy wave effect is negligible.

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Section: Generated Disturbancesupporting

confidence: 72%

Transport of Swirling Entropy Waves through an Axial Turbine Stator

Notaristefano

Gaetani

2021

IJTPP

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“…In Ref. [23], additional loss cores were observed with swirl; these were attributed to interaction between the swirl vortex and the HP vane (rather than interaction between the swirl vortex and the cooling flows). Similar interactions were reported in the linear cascade study reported by Jacobi et al [24].…”

Section: Introductionmentioning

confidence: 98%

“…Experiments have been conducted using a 1.5-stage research turbine with film-cooled HP vanes and endwalls. These studies have focused on the robustness of the endwall cooling system to swirl [22] and on the total pressure losses and vane and endwall coolant migration with swirl [23]. Both studies reported significant reductions in endwall cooling effectiveness with swirl: coolant was redistributed, leaving some surfaces virtually uncooled.…”

Section: Introductionmentioning

confidence: 99%

Effect of a Combined Hot-Streak and Swirl Profile on Cooled 1.5-Stage Turbine Aerodynamics: An Experimental and Computational Study

Adams

Beard

Stokes

et al. 2021

Journal of Turbomachinery

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Recently developed lean-burn combustors offer reduced NOx emissions for gas turbines. The flow at exit of lean-burn combustors is dominated by hot-streaks and residual swirl, which have been shown–individually–to impact turbine aerodynamic performance. Studies have shown that residual swirl at inlet to the high-pressure (HP) stage predominantly affects the vane aerodynamics, while hot-streaks affect the rotor aerodynamics. Studies have also shown that these changes to the HP stage aerodynamics can affect the downstream intermediate-pressure (IP) vane aerodynamics. Yet, to date, there have been no published studies presenting experimental turbine test data with both swirl and hot-streaks simultaneously present at inlet. This paper presents the first experimental and computational investigation into the effects of combined hot-streaks and swirl on turbine aerodynamics. Measurements were conducted in the Oxford Turbine Research Facility, a short-duration rotating transonic facility that matches non-dimensional engine conditions. Two turbine inlet flows are considered. The first is uniform in total pressure, total temperature, and flow angle. The second features a non-uniform total temperature (hot-streak) profile featuring strong radial and weak circumferential variation superimposed on a swirling velocity profile. Area surveys of the flow were conducted throughout the turbine. Measurements and URANS predictions suggest that the inlet temperature non-uniformity was relatively well preserved upon being convected through the turbine, and relatively poor comparisons between URANS and experiment highlight the challenge of accurately predicting the complex IP vane flow.

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“…The large scale turbine rig at the Technical University Darmstadt, described by Krichbaum et al [18], has been used for several detailed studies of combustor-turbine interactions effect on time-averaged quantities. Werchnik et al [19,20,21] traced cooling flows and measured Nusselt number and cooling effectiveness with different amounts of film cooling with axial and swirling inflow.…”

Section: Introductionmentioning

confidence: 99%