Review of Gas Turbine Internal Cooling Improvement Technology

Nourin, Farah Nazifa; Amano, Ryoichi S.

doi:10.1115/1.4048865

Cited by 50 publications

(14 citation statements)

References 29 publications

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Section: Literature Reviewmentioning

confidence: 99%

“…Hence, the gas temperature at the turbine inlet decreases without loss of power, which favorably affects the gas turbine resource or it becomes possible to increase the gas turbine power without reducing the resource of its operation. 10 Cyclic air cooling allows to reduce the specific fuel consumption and increase the engine's power output 11,12 that is especially important for the changing climatic conditions of the engine operation. 13,14 The compressor operation or its individual stages is proportional to the inlet temperature.…”

Section: Literature Reviewmentioning

confidence: 99%

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Research of characteristics of the flow part of an aerothermopressor for gas turbine intercooling air

Konovalov

Radchenko

Kobalava

et al. 2021

Proceedings of the Institution of Mechanical Engineers, Part A:

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Complex gas turbine schemes with air intercooling are usually used to bring the compression process of working fluid in compressor closer to isothermal one. A promising way to realize it is to use an aerothermopressor. The aerothermopressor is a two-phase jet apparatus, in which the highly dispersed liquid (water) is injected into the superheated gas (air) stream accelerated to the speed closed to the sound speed value (Mach number from 0.8 to 0.9). The air pressure at the aerothermopressor outlet (after diffuser) is higher than at the inlet due to instantaneous evaporation of highly dispersed liquid practically without friction losses in mixing chamber and with an increase in pressure of the mixed homogenous flow. The liquid evaporation is conducted by removing the heat from the air flow. In the course of the experimental research, the operation of the aerothermopressor for gas turbine intercooling air was simulated and its characteristics (hydraulic resistance coefficients, pressure increase, and air temperature) were determined. Within contact cooling of air in the aerothermopressor, the values of the total pressure increase in the aerothermopressor were from 1.02 to 1.04 (2–4%). Thus, the aerothermopressor use to provide contact evaporative cooling of cyclic air between the compressor stages will ensure not only compensation for pressure losses but also provides an increase in total air pressure with simultaneous cooling. Injection of liquid in a larger amount than is necessary for evaporation ensures a decrease in pressure losses in the flow path of the aerothermopressor by 15–20%. When the amount of water flow is more than 10–15%, the pressure loss becomes equal to the loss for the “dry” aerothermopressor, and with a further increase in the amount of injected liquid, they are exceeded. The values of errors in the relative increase of air pressure in the aerothermopressor measurements not exceeded 4%. The results obtained can be used in the practice of designing intercooling systems for gas turbines.

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Section: Literature Reviewmentioning

confidence: 99%

Section: Literature Reviewmentioning

confidence: 99%

Research of characteristics of the flow part of an aerothermopressor for gas turbine intercooling air

Konovalov

Radchenko

Kobalava

et al. 2021

Proceedings of the Institution of Mechanical Engineers, Part A:

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“…Simultaneously, the necessity to ensure minimum impedance and losses in the thermodynamic performances of the turbine is vital as well. Researchers have been working for many years to find and fine tune designs for the cooling channels that provide high transfer, while minimize the pressure drop [2]. This is possible only by enhancing the gas's turbine inlet temperature (TIT), which ensures that the work done by the turbine in the expansion process is high.…”

Section: Introductionmentioning

confidence: 99%

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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“…The gas turbine runs at exceptionally high temperatures between 1600 K and 1900 K in order to improve the efficiency of the turbine [2]. However, higher operating temperature of the gas turbine can lead to wear, failure and fatigue of the turbine blade after a certain period of time [3]. This constraint renders cooling in gas turbine systems a critical field of heat transfer research.…”

Section: Introductionmentioning

confidence: 99%

“…The cooling system plays a key role in maintaining the turbine components temperature below critical level and in avoiding overheating failure [4]. Several internal cooling methods may be used to improve the heat transfer of turbine blades, including rib turbulators, pin fins, dimples and jet impingement cooling [3,5]. Previously, the authors have studied the use of palm oil to reduce the friction rate in the system.…”

Section: Introductionmentioning

confidence: 99%

Experimental Investigation of the Effectiveness of Jet Impingement Cooling System on the Pressure Side of the Turbine Blade

Kamalulzaman

Azman

Musa

et al. 2021

ARFMTS

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The effectiveness of the jet impingement system on the turbine blade pressure side has been experimentally investigated. The effects of height-to-diameter ratio and air velocity on the effectiveness of jet impingement were studied. Experiments was performed under varying height-to-diameter ratios (H/D = 5, 10, 15, 20) where the distance from the nozzle to the pressure side surface ranged from 20, 40, 60 and 80 mm with a constant nozzle diameter of 4 mm. The Nusselt number is calculated to determine the cooling effect of the pressure side model surface. Experiments were also performed at varying air velocity at 6.4 m/s and 12.6 m/s. The findings revealed that there was no direct relationship between Nusselt number and H/D ratio where the optimum cooling impact at a velocity of 6.4 m/s was found to be at H/D=15, whereas at a velocity of 12.6 m/s it was found to be at H/D=5. The findings also reveal that the amount of Nusselts rises as the air velocity increases.

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Review of Gas Turbine Internal Cooling Improvement Technology

Cited by 50 publications

References 29 publications

Research of characteristics of the flow part of an aerothermopressor for gas turbine intercooling air

Research of characteristics of the flow part of an aerothermopressor for gas turbine intercooling air

Comprehensive Review on Leading Edge Turbine Blade Cooling Technologies

Experimental Investigation of the Effectiveness of Jet Impingement Cooling System on the Pressure Side of the Turbine Blade

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