Effects of the novel rib layouts on the tip leakage flow pattern and heat transfer performance of turbine blade

Jiang, Shijie; Li, Zhigang; Li, Jun; Song, Liming

doi:10.1177/0954410020910883

Cited by 11 publications

(3 citation statements)

References 26 publications

(41 reference statements)

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“…The rib number and installation angle have significant influences on the aero-thermal performance of squealer tip. Then, Du et al 24 and Jiang et al 25 numerically investigated the aero-thermal performance of the multi-cavity squealer tip in a turbine stage. Their results suggested that the rib location and geometry significantly affect the aero-thermal performance of squealer tip.…”

Section: Introductionmentioning

confidence: 99%

Modifications of double-rim geometry to improve thermal performance of squealer tip in a turbine stage

Yan

2023

Proceedings of the Institution of Mechanical Engineers, Part A:

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The double-recessed (i.e. double-rim) design is an alternative to improve thermal performance of the squealer tip. In this paper, the aero-thermal performance of double-rim squealer tip in a turbine stage was numerically investigated under engine condition. The heat transfer and film cooling effect between the double-rim squealer tip and conventional squealer tip were compared to show the superior thermal characteristic of double-rim design. The interactions between the leakage flow and coolants were analyzed to address the heat transfer reduction and film cooling improvement for the double-rim configuration. To further reduce the thermal load on double-rim squealer tip, the height and arc length of the inner rim were modified to increase the coolant accumulations in squealer cavities. The results show that the tip and pressure side cooling flow is well attached on the cavity floor and suction side rim of double-rim squealer tip as compared to the conventional squealer tip. With the proper arrangement of inner rim height and arc length, the modified double-recessed squealer tip helps to reduce the area-averaged heat transfer coefficient by 90.3%, and improve the film cooling effectiveness by 49.6%, while the isentropic stage efficiency is almost not affected, as compared to the conventional squealer tip.

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Section: Introductionmentioning

confidence: 99%

Modifications of double-rim geometry to improve thermal performance of squealer tip in a turbine stage

Yan

2023

Proceedings of the Institution of Mechanical Engineers, Part A:

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“…[7][8][9] In the early stage, researchers studied the effect of single side squealer tip on TLF through experiments and numerical methods and found that the suction side squealer tip has a better blocking effect on the TLF. 10,11 Then, more and more researchers focused on the geometric optimization of the squealer tip, such as the number and layout of rims, [12][13][14] cutback configurations, 15,16 and the width and depth of rims. 17,18 The researchers from the von Karman Institute for Fluid Dynamics (VKI) [19][20][21] tried to optimize the squealer-like tip geometry by using the differential evolution algorithm and finally obtained the double-cavity tip configuration with great aerodynamic and thermal performance.…”

Section: Introductionmentioning

confidence: 99%

Effects of inclined squealer rims on tip leakage vortex and loss in a transonic axial turbine

Wang

Zhang

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part A:

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In this paper, to investigate the effects of inclined squealer rims on tip leakage flow and loss, numerical simulations have been performed on a transonic high-pressure turbine. Based on the geometry of prototype with conventional cavity tip, six modifications with different inclined rims are constructed. The effects of inclined suction side squealer rim (SSSR) on tip leakage flow (TLF) is analyzed emphatically. The results show that it is advantageous to control the TLF and loss if the internal and external surface of SSSR are inclined in a proper direction. When the internal surface of SSSR is inclined toward the cavity, the scraping vortex and its pneumatic labyrinth sealing effect are enhanced, which is beneficial to blocking the TLF and reducing the mixing loss. As the external surface of SSSR is inclined toward the passage, the pressure gradient near the tip changes and the intensity of adverse pressure gradient decreases, which is conducive to suppressing the breakdown of tip leakage vortex (TLV). In addition, the inclined external surface could make the TLV away from the blade and reduce the viscous dissipation. Regarding the aerodynamic performance of the turbine, the inclined pressure side squealer rim (PSSR) could improve the stage efficiency of the turbine by 0.08% relative to the prototype, while the proper inclined SSSR could further improve that by 0.18%.

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“…Du et al 20 added riblet design perpendicular to tip camber line to effectively segment high heat transfer stripe, thus improving overall heat transfer effect of blade tip. Jiang et al 21 continued to optimize rib size inside blade tip and further reduced tip heat transfer coefficient by reducing rib length in tip trailing region. Park et al 22,23 also studied blade tip rib design on tip aerothermal performance.…”

Section: Introductionmentioning

confidence: 99%

Effect of casing purge flow on heat transfer and cooling performance of blade squealer tip for a gas turbine stage

Jiang

2021

Proceedings of the Institution of Mechanical Engineers, Part A:

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The first stage of GE-E3 turbine is employed to investigate effect of casing purge flow upstream rotor blade tip. Three-dimensional Reynolds-averaged Navier-Stokes (RANS) equations and standard k-ω model are solved to obtain tip heat transfer simulations. The results reveal that: heat transfer coefficient of blade tip surface can be significantly reduced when casing purge flow is set. Tip averaged heat transfer coefficient of cases with and without swirly velocity casing purge flow decrease 3.5% and 3.4% compared with the case without casing purge flow. Compared with case which blowing ratio equals to 0.5, it can be found that averaged tip heat transfer coefficient of cases which blowing ratio equals to 1.0 and 1.5 decrease 2.3% and 1.8%, respectively. Setting blowing ratio as 1.0 can best cool tip surface without wasting cold air resources. Increasing rotating speed can induce cold air entering tip trailing region and improve local cooling effect. Flow structure inside the tip clearance are also revealed and discussed.

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Effects of the novel rib layouts on the tip leakage flow pattern and heat transfer performance of turbine blade

Cited by 11 publications

References 26 publications

Modifications of double-rim geometry to improve thermal performance of squealer tip in a turbine stage

Modifications of double-rim geometry to improve thermal performance of squealer tip in a turbine stage

Effects of inclined squealer rims on tip leakage vortex and loss in a transonic axial turbine

Effect of casing purge flow on heat transfer and cooling performance of blade squealer tip for a gas turbine stage

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