A review of cooling technologies for high temperature rotating components in gas turbine

Unnikrishnan, Umesh; Yang, Vigor

doi:10.1016/j.jppr.2022.07.001

Cited by 68 publications

(17 citation statements)

References 111 publications

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“…The high temperature rises and low emissions are the development trend of combustors. Therefore, to develop more efficient gas turbines that better protect combustors and turbine blades from erosion in high-temperature environments while extending their service life, it is necessary to develop efficient cooling systems for gas turbines [3,4]. Cooling holes play a crucial role in maintaining safe operating temperatures for engine components [5,6].…”

Section: Introductionmentioning

confidence: 99%

Improving Film Cooling Efficiency with Lobe-Shaped Cooling Holes: An Investigation with Large-Eddy Simulation

Wang

Zhao

et al. 2023

Applied Sciences

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Shaped cooling holes have received considerable attention in recent years due to their potential to improve heat transfer while minimizing pressure drop. In this study, the effects of lobe-shaped cooling holes on film cooling performance and turbulent flow characteristics are investigated using large-eddy simulation (LES). The LES approach was validated by comparing the calculated film cooling effectiveness with experimental data. The results show that well-designed lobe-shaped cooling holes can improve the cooling efficiency by up to 37% and reduce the total pressure drop. Additionally, the cooling jets of lobe-shaped cooling holes have a smaller angle to the wall surface, indicating better wall attachment. However, poorly designed lobe-shaped cooling holes can reduce the cooling efficiency. Overall, this study suggests that lobe-shaped cooling holes are a promising technology for improving gas turbine engine performance.

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Section: Introductionmentioning

confidence: 99%

Improving Film Cooling Efficiency with Lobe-Shaped Cooling Holes: An Investigation with Large-Eddy Simulation

Wang

Zhao

et al. 2023

Applied Sciences

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“…Aircraft engines, gas turbines, and hypersonic vehicles often operate in harsh environments with high temperatures, heavy loads, and strong vibrations. – High-temperature components, such as engine blades, that work directly in such severe environments may get deformed, cracked, or even shattered and fail, reducing the equipment’s service life and safety. , Strain sensors can detect stress and deformation in a variety of applications, including biological applications, , structural health testing, , electronic skin, , etc. Therefore, online monitoring of stress/strain on high-temperature components operating in harsh environments can aid in early defect detection for equipment maintenance and ensure the equipment’s safe operation.…”

Section: Introductionmentioning

confidence: 99%

Conformal Fabrication of Thick Film Platinum Strain Gauge Via Error Regulation Strategies for In Situ High-Temperature Strain Detection

Chen,

Zhao,

Zeng

et al. 2023

ACS Appl. Mater. Interfaces

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Monitoring high-temperature strain on curved components in harsh environments is a challenge for a wide range of applications, including in aircraft engines, gas turbines, and hypersonic vehicles. Although there are significant improvements in the preparation of high-temperature piezoresistive film on planar surfaces using 3D printing methods, there are still difficulties with poor surface compatibility and high-temperature strain testing on curved surfaces. Herein, a conformal direct ink writing (CDIW) system coupled with an error feedback regulation strategy was used to fabricate high-precision, thick films on curved surfaces. This strategy enabled the maximum amount of error in the distance between the needle and the substrate on a curved surface to be regulated from 155 to 4 μm. A conformal Pt thick-film strain gauge (CPTFSG) with a room-temperature strain coefficient of 1.7 was created on a curved metallic substrate for the first time. The resistance drift rate at 800 °C for 1 h was 1.1%, which demonstrated the excellent stability and oxidation resistance of the CPTFSG. High-temperature dynamic strain tests up to 769 °C revealed that the sensor had excellent high-temperature strain test performance. Furthermore, the CPTFSG was conformally deposited on an aero-engine turbine blade to perform in situ tensile and compressive strain testing at room temperature. High-temperature strain tests were conducted at 100 and 200 °C for 600 and 580 με, respectively, demonstrating a high steady-state response consistent with the commercial high-temperature strain transducer. In addition, steady-state strain tests at high temperatures up to 496 °C were tested. The CDIW error modulation strategy provides a highly promising approach for the high-precision fabrication of Pt thick films on complex surfaces and driving in situ sensing of hightemperature parameters on curved components toward practical applications.

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“…Design of the blade cooling system must provide the more intensive heat extraction in the heat-loaded areas [12,13]. Some cases need the additional heat transfer intensification on the pressure side and other cases need it on the suction side.…”

Section: Introductionmentioning

confidence: 99%

Asymmetric Method of Heat Transfer Intensification in Radial Channels of Gas Turbine Blades

Osipov

Rogalev

et al. 2022

Inventions

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Loop and semi-loop cooling schemes are widely used for the high-temperature gas turbine blades. In such schemes, the mid-chord airfoil parts are traditionally cooled by radial channels with ribbed walls. The blades with a small specific span, or “short” blades, have different heat flux amounts on pressure and suction sides, which results in a temperature difference in these sides of 100–150 °K. This difference causes thermal stresses and reduces the long-term strength margins. This paper presents a new method of heat transfer intensification in the ribbed radial cooling channels. The method is based on air streams’ injection through holes in the ribs that split channels. The streams are directed along the walls into the stagnation zones behind the ribs. The results of a 3D coolant flow simulation with ANSYS CFX code show the influence of the geometry parameters upon the channel heat transfer asymmetry. In the Reynolds number within a range of 6000–20,000, the method provides the heat transfer augmentation difference by up to 40% on the opposite channel walls. Test results presented in the criteria relations form allow for the calculation of mean the heat transfer coefficient along the channel length.

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A review of cooling technologies for high temperature rotating components in gas turbine

Cited by 68 publications

References 111 publications

Improving Film Cooling Efficiency with Lobe-Shaped Cooling Holes: An Investigation with Large-Eddy Simulation

Improving Film Cooling Efficiency with Lobe-Shaped Cooling Holes: An Investigation with Large-Eddy Simulation

Conformal Fabrication of Thick Film Platinum Strain Gauge Via Error Regulation Strategies for In Situ High-Temperature Strain Detection

Asymmetric Method of Heat Transfer Intensification in Radial Channels of Gas Turbine Blades

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