Turbine Blade Tip External Cooling Technologies

Xue, Song; Ng, Wing Fai

doi:10.3390/aerospace5030090

Cited by 17 publications

(11 citation statements)

References 71 publications

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“…The connected turbine blades [7,8] each inside and far, Figure 1 shows the common cooling structure that exists and the three internal cooling zones that are essential to the turbine blade with the most important film [4,9,10] within the front edge, weight and shaving areas, and in the edge region. The large edge is cooled using the turbulence [4,11] and film coating [7,12], the middle section is covered with infinite sections blocked by ribs with traditional film coating, and the edge is cooled with the help of pine pins using the twisting edge. Internal cooling basically, transfers the coolant through many small pores inside the stains and removes heat from the surface of the stains.…”

Section: Gas Turbine Blade Cooling -Externally and Internallymentioning

confidence: 99%

“…It [4,9,13] is a prevalent technology that allow modern gas circulation engines to achieve greater temperatures with shooting, high efficiency, and longevity. In the rotating engine of a cold film [7,12], it is like the cool air from inner side of the case to the outer surface, eventually safeguarding like a protective layer cool between the newly formed gases and the outer part. These film patterns [4,12] (e.g., film location, distribution, angle, and position) contribute to the cooling performance of the film [12].…”

Section: Film Coolingmentioning

confidence: 99%

“…In a broader sense, the surface of the concavity flows in one large area called the vortex technology [5,13], which includes multiple pathways which means the establishment of vertical flow or rotating turbines [5]. Another rising vortex technology [12] is that the use of different wall jets is embedded in the bursiform cooling pads, or in parts of the inner wall to make the most complete movements. This cooling method is commonly referred to as swirl cooling [12,13], and in addition the cooling of the hurricane provides equilibrium with equal heat transfer in which a direct impact is applied [12].…”

Section: Swirl Coolingmentioning

confidence: 99%

See 2 more Smart Citations

Comprehensive Review on Leading Edge Turbine Blade Cooling Technologies

Sharma¹,

Kumar²,

Singh³

et al. 2021

IJHT

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Developments in the gas turbine technology have caused widespread usage of the Turbomachines for power generation. With increase in the power demand and a drop in the availability of fuel, usage of turbines with higher efficiencies has become imperative. This is only possible with an increase in the turbine inlet temperature (TIT) of the gas. However, the higher limit of TIT is governed by the metallurgical boundary conditions set by the material used to manufacture the turbine blades. Hence, turbine blade cooling helps in drastically controlling the blade temperature of the turbine and allows a higher turbine inlet temperature. The blade could be cooled from the leading edge, from the entire surface of the blade or from the trailing edge. The various methods of blade cooling from leading edge and its comparative study were reviewed and summarized along with their advantages and disadvantages.

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Section: Gas Turbine Blade Cooling -Externally and Internallymentioning

confidence: 99%

Section: Film Coolingmentioning

confidence: 99%

Section: Swirl Coolingmentioning

confidence: 99%

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Comprehensive Review on Leading Edge Turbine Blade Cooling Technologies

Sharma¹,

Kumar²,

Singh³

et al. 2021

IJHT

View full text Add to dashboard Cite

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“…Therefore, appropriate cooling techniques must be used in order to reduce the thermal damages to the blades and to sustain reasonable operational life. [1][2][3][4][5][6] The blade tip is particularly exposed to much higher heat transfer compared to the rest of the blade surface and hence it is considered as a critical design area within the high pressure turbine. One way to seal the blade tip is to interconnect the blades using a shroud.…”

Section: Introductionmentioning

confidence: 99%

Effect of in-service burnout effect on the transonic leakage flows over cavity tip model

Saleh

Avital

Korakianitis

2021

Proceedings of the Institution of Mechanical Engineers, Part A:

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Increasing the gas temperature at the inlet to the high pressure turbine of gas turbine engines is known as a proven method to increase the efficiency of these engines. However, this will expose the blades’ surface to very high heat load and thermal damages. In the case of the un-shrouded turbine blades, the blade tip will be exposed to a significant thermal load due to the developed leakage flows in the tip gap, this leads to in-service burnout which degrades the blade tip and shortens its operational life. This paper studies the in-service burnout effect of the transonic tip flows over a cavity tip which is a configuration commonly used to reduce the tip leakage flows. This investigation is carried out experimentally within a transonic wind tunnel and computationally using steady and unsteady Reynolds Averaged Navier Stokes approaches. Various flow measurements are established and different flow behaviour including separation bubbles, shockwave development and distinct flow interactions are captured and discussed. It is found that when the tip is exposed to the in-service burnout, leakage flow behaves in a significantly different way. In addition, the effective tip gap becomes much larger and allows higher leakage mass flow rate in comparison to the sharp-edge tip (i.e. a tip at the beginning of its operational life). The tip leakage losses are found much higher for the round-edge cavity tip (i.e. a tip exposed to burn-out effect). Experimental and computational flow visualisations, surface pressure measurements and discharge coefficient variation are given and analysed for several pressure ratios across the tip gap.

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“…However, despite this advantage, this approach will also expose the blades to high-temperature and high-heat transfer and requires suitable cooling techniques for the blade material to sustain a sufficiently long operational life. 1–4…”

Section: Introductionmentioning

confidence: 99%

Effect of in-service burnout on the transonic tip leakage flows over flat tip model

Saleh

Avital

Korakianitis

2019

Proceedings of the Institution of Mechanical Engineers, Part A:

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Un-shrouded turbine blades are more common than shrouded ones in gas turbine aero-engines since they reduce the weight and avoid the centrifugal loading caused by the blades’ shrouds. Despite these important advantages, the absence of the shroud leads to leakage flows across the tip gap and exposes the blade tip to high thermal load and thermal damages. In addition, the leakage flows can contribute up to 30% of the aerodynamic loss in a turbine stage. In this study, the effect of in-service burnout is explored using a fundamental flat tip model of a high-pressure gas turbine blade. This investigation is carried out both experimentally in a transonic wind tunnel and computationally using the Reynolds Averaged Navier-stokes approach at high-speed conditions. It is found that exposing the tip to the in-service burnout effect changes the leakage flow behaviour significantly when compared with the tip with sharp edges (i.e. the tip at the start of its operational life). Different flow acceleration, flow structure and shockwave pattern and interactions are captured for the round-edge flat tip (i.e. the tip exposed to in-service burnout). The effective tip gap is found to be much larger for the round-edge flat tip allowing more leakage flow into the tip gap which results into higher tip leakage losses in comparison to the sharp-edge tip. Experimental and computational flow visualisations, surface pressure distributions and discharge coefficient are given and analysed for several pressure ratios over the tip gap.

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Turbine Blade Tip External Cooling Technologies

Cited by 17 publications

References 71 publications

Comprehensive Review on Leading Edge Turbine Blade Cooling Technologies

Comprehensive Review on Leading Edge Turbine Blade Cooling Technologies

Effect of in-service burnout effect on the transonic leakage flows over cavity tip model

Effect of in-service burnout on the transonic tip leakage flows over flat tip model

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