The Combined Influences of Hot Streak and Swirl on the Cooling Performances of C3X Guide Vane with or without TBCs

Shi, Li; Huang, Hanze; Lu, Yuanfeng; Xu, Sheng; Chen, Ge

doi:10.3390/coatings11060688

Cited by 4 publications

(3 citation statements)

References 24 publications

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“…This is primarily attributed to the flow acceleration originating from the stagnation line on the SS. Shi et al [22] conducted experiments on the inlet plane of the passage; the presence of positive swirls resulted in an elevated temperature in the tip region on the SS. Conversely, when a negative swirl was introduced, it led to a higher temperature in the hub region on the PS.…”

Section: Introductionmentioning

confidence: 99%

Impact of Swirling Flow on the Overall Cooling Effectiveness and TBCs Insulation Characteristics of Turbine Vane

Shi,

Wu,

Huang

et al. 2023

Coatings

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Modern gas turbines find extensive applications in aero engines, power generation, marine, and various other industries. Most numerical studies concentrate on turbine aero-thermal performance under different external conditions with vane or coupon; there are a few published results on combustor-turbine interactions. This study reveals the cooling performance of the first stage with or without coatings to provide a reference for high-performance combustors and turbine-integrated design. The results of the study show that (1) The velocity and temperature distribution inside the combustion chamber are obviously affected by the swirling flow. A central recirculation zone is formed near the central axis, and two external recirculation zones are formed between the inlet section of the combustion chamber and the fluid reattachment point. (2) Inside the combustion chamber, the flame temperature in the central recirculation zone is relatively high, and the range of the high-temperature zone expands with the increase of axial distance. Increasing the swirl number decreases the peak temperature level in the combustion chamber. (3) Under the influence of swirl number, the greater the swirl number, the greater the cooling effectiveness of most areas on the vane surface. (4) In regions where there is a decrease in local heat flux, positive values are evident. This suggests that the application of a coating in these areas results in a reduction of heat transfer from the vane to the mainstream. (5) When comparing the coated vane to the uncoated vane, the cooling effectiveness across the entire surface is notably enhanced, with a particularly significant improvement observed on the vane’s suction side. With the increase of Cax, the difference in cooling effectiveness increment under different swirl numbers also increases.

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Section: Introductionmentioning

confidence: 99%

Impact of Swirling Flow on the Overall Cooling Effectiveness and TBCs Insulation Characteristics of Turbine Vane

Shi,

Wu,

Huang

et al. 2023

Coatings

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show abstract

“…They concluded that the HS significantly increased the non-uniformity of the heat load distribution over the blade surface. Shi [12] studied the effect of the HS on the overall cooling performance of the turbine vane additional TBCs and film cooling. They concluded that TBCs could reduce the influence of the hot streaks on the overall cooling performance.…”

Section: Introductionmentioning

confidence: 99%

Effect of the Hot Streak on the Overall Cooling Performance of a Coated Rotor Blade

Shi

Huang

2022

Energies

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The influence of the HS (hot streak) and unsteady wake on the overall cooling performance of a rotor blade was studied in this paper. The results show that: (1) Both the magnitude and temperature of the HS gradually drops down as it passes downstream of the vane passage. (2) Within one stator period, the highest cooling performance of the blade can be observed at the initial time points, when the LE (leading edge) of the blade turns towards the trailing edge of the vane. (3) The lowest cooling performance of the blade can be observed at the time point 0.5 T, when the LE of the blade turns towards the center of the vane passage. (4) Surface temperatures in areas with unfavorable local heat flow are usually higher than the temperature of the coolant. The additional TBCs may exert adverse effects on heat dissipation from the substrate metal to the mainstream, which has a negative effect on the improvement of the overall cooling effectiveness of the coated blade. (5) Within a stator period, a relatively higher overall cooling effectiveness increment due to the coating can be observed at the relative location with lower cooling performance. Consequently, the additional TBCs are beneficial for decreasing the surface temperature difference and thus controlling the thermal stress under the HS inlet condition.

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“…In the studies that have been performed, more attention has been placed on the uncoated vane. Information on the influence on the coated stator vane and the coated rotor blade is still less common in the open literature, especially for the coated rotor blade [18][19][20][21]. For the coated rotor blade, a wide variety of factors are known to contribute to the complexity of aerothermal and TBC insulation performance, which include the hot streak, the residual swirl, high levels of mainstream turbulence and unsteadiness, rotational effects, and rotor-stator interaction [22][23][24][25][26].…”

Section: Introductionmentioning

confidence: 99%

Analysis of Rotor–Stator Interaction on the Aerothermal and TBC Insulation Performance of a Turbine Stage under Hot Streak Inlet Condition

Shi

Huang

2021

Coatings

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Hot streaks and rotor–stator interaction have a great influence on the aerothermal performance of turbine blades. Previous investigations have conducted limited study of the film-cooled blade. To investigate the combined effects of a hot streak and rotor–stator interaction on the coated blade, an unsteady numerical simulation has been conducted with an efficient unsteady Navier–Stokes solver in this paper. The numerical results at four different relative stator–rotor locations (t = 0/4 T, 1/4 T, 2/4 T, and 3/4 T) have been investigated in one stator period. Compared with the stator, rotor–stator interaction exerts a significant impact on the cooling performance of the rotor blade under hot streak inlet conditions. The overall cooling effectiveness distribution of the coated rotor blade is similar to that of the uncoated blades in one stator period. Relatively lower overall cooling performance of the rotor blade can be observed in the 1/4 stator period. Then, the cooling performance begins to increase and relatively larger cooling effectiveness can be observed in the 3/4 stator period. The addition of a TBC is generally beneficial to the improvement of blade surface cooling performance, especially for the areas with low overall cooling performance. However, a negative cooling effectiveness increment can be observed at the trailing edge. It shows that for an area with poor cooling performance, the addition of thermal barrier coating will have the opposite effect. Therefore, it is necessary to enhance the design of cooling arrangements at the trailing edge to maximize the insulation performance of TBCs for the coated rotor blade.

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The Combined Influences of Hot Streak and Swirl on the Cooling Performances of C3X Guide Vane with or without TBCs

Cited by 4 publications

References 24 publications

Impact of Swirling Flow on the Overall Cooling Effectiveness and TBCs Insulation Characteristics of Turbine Vane

Impact of Swirling Flow on the Overall Cooling Effectiveness and TBCs Insulation Characteristics of Turbine Vane

Effect of the Hot Streak on the Overall Cooling Performance of a Coated Rotor Blade

Analysis of Rotor–Stator Interaction on the Aerothermal and TBC Insulation Performance of a Turbine Stage under Hot Streak Inlet Condition

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