Modification and optimization strategies for turbine arbitrary blade tips

Jin, Jiahui; Song, Yanping; Yu, Jianyang; Chen, Fu

doi:10.1177/0957650919826326

Cited by 4 publications

(2 citation statements)

References 16 publications

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“…Du et al (2021a); Du et al (2021b) systematically illustrated the cooling and impact effects of air film pores in the blades. Jin et al (2019) numerically studied the influence of different arbitrary blade tip shapes on restraining the tip leakage flow in a highly loaded turbine cascade. Kumar et al (2020) presented the thermomechanical analysis of a typical SGT engine to study the blade tip clearance influenced by the deformation of turbine stage components (turbine rotor and nozzle guide vane (NGV) with integral blade shroud) during transient phases.…”

Section: Introductionmentioning

confidence: 99%

Effect of Film Position on the Flow and Heat Transfer Characteristics of Full-Ribbed Rotor Tip

et al. 2022

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This article numerically studied the flow and heat transfer characteristics of the full-ribbed fluted tip of a rotor with four types of distribution of cooling films, namely, the mid-arc uniform film at the bottom of the groove, the uniform film on full perimeter ribs, the uniform film on the suction-side rib, and the uniform film on the pressure-side rib. The evolution of secondary flow in the tip clearance under these four conditions was discussed, and the effect of cooling film position on the tip leakage flow and tip heat transfer was also studied. The results showed that films in the ribs were more conducive to lower leakage flow rates and can reduce total energy losses. Adding cooling films on the single-side rib had a better effect on the control of leakage flow rate, with the most significant improvement due to adding cooling films on the suction-side rib. The mid-arc jet at the bottom of the groove can greatly contain the swirl structure in the groove, but it weakened the air sealing effect, which led to a rise in leak flow. The main reason for the swirl structure in the groove was that the leakage flow from the tip of the rotor was blocked by the cold air jet from the cooling films to form a backflow. The vortex inside the groove was the most violent when the air film hole was set on the pressure side, so the loss coefficient was higher, while the vortex inside the groove was the simplest when the cooling film hole was set on the suction side, and the energy loss caused by the vortex inside the groove was the least, and this structure was more favorable to the cooling of the leaf tip. It was also found that the uniformity of the outlet airflow angle distribution improved in the presence of cold air injection on the tip of the rotor.

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Section: Introductionmentioning

confidence: 99%

Effect of Film Position on the Flow and Heat Transfer Characteristics of Full-Ribbed Rotor Tip

et al. 2022

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“…Compared with the flat tip, the efficiency was increased by 0.15% and 0.3%, respectively. Jin 29, 30 applied the trigonometric curves and the B-spline surface to the tip structure and obtained the optimal novel tips by the Kriging model and the genetic optimization algorithm. In this paper, four kinds of the blade tip structures have been studied through the experimental tests and the numerical analysis, including the flat tip (FT), the squealer tip (ST), the optimal mathematical tip (OMT) and the optimal B-spline tip (OBT).…”

Section: Introductionmentioning

confidence: 99%

Experimental and numerical study of novel tip configurations in a turbine cascade

Jin

Song

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part A:

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Two novel tip modeling methods are proposed in this paper. One novel tip is established by the mathematical method and the other is generated by the B-spline surface. And the genetic algorithm, the orthogonal design and the Kriging model are applied to optimize two kinds of novel tips numerically. The optimal mathematical tip and the optimal B-spline tip are acquired respectively. The aerodynamic tests were investigated at the wind tunnel test section, including the flat tip, the squealer tip, the optimal mathematical tip and the optimal B-spline tip. The static pressure distributions on the casing and the blade surface were measured by the pressure taps. Meanwhile, the secondary flow and the loss were obtained by the five-hole probe at the exit section. A comparison of the simulation analysis results with the experimental results shows good agreement. Compared with the flat tip, the measured loss on the squealer tip, the optimal mathematical tip and the optimal B-spline tip is decreased by 7.2%, 10.5% and 12.6% respectively.

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Parameter optimization of the composite honeycomb tip in a turbine cascade

Wang

Song

et al. 2020

Energy

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Modification and optimization strategies for turbine arbitrary blade tips

Cited by 4 publications

References 16 publications

Effect of Film Position on the Flow and Heat Transfer Characteristics of Full-Ribbed Rotor Tip

Effect of Film Position on the Flow and Heat Transfer Characteristics of Full-Ribbed Rotor Tip

Experimental and numerical study of novel tip configurations in a turbine cascade

Parameter optimization of the composite honeycomb tip in a turbine cascade

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