Film cooling characteristics on the leading edge of a rotating turbine blade with various mainstream Reynolds numbers and coolant densities

Li, Haiwang; Han, Feng; Wang, Haichao; Zhou, Zhiyu; Tao, Zhi

doi:10.1016/j.ijheatmasstransfer.2018.07.126

Cited by 23 publications

(8 citation statements)

References 25 publications

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“…Among them, passive thermal protection mainly includes the application of ceramic matrix composite (CMC) in the combustion chamber of ramjets and sharp suction pipelines [15], and the application of high silicon/phenolic materials on turbine engines and solid rocket motors [16]. Active thermal protection mainly includes the application of sweat cooling in the combustion chamber, the application of air film cooling [17] on turbine blades [18,19], and the application of convective cooling [20] in the combustion chamber and cooling channel [21]. Thermal barrier coating technology is widely used in hot components such as turbine blades, combustion chambers, and air inlets in a combined propulsion system [22].…”

Section: Overviewmentioning

confidence: 99%

Thermal Protection System and Thermal Management for Combined-Cycle Engine: Review and Prospects

et al. 2019

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Combined-cycle engine is a potential propulsion system for hypersonic aircraft. To ensure long-term, normal operation of combined-cycle engine under the harsh environment of high thermal load, it is of great significance to study the thermal protection and management of the propulsion system. In this study, the objective and development status of thermal protection and thermal management systems for the combined-cycle propulsion system were described. The latest research progresses of thermal protection, thermal barrier coating, and thermal management system of the combined-cycle propulsion system were summarized. Moreover, the problems and shortcoming in current researches were summarized. In addition, a prospect for the future development of thermal protection and management of the combined-cycle propulsion system was presented, pointing out a direction of great value and vital research significance to thermal protection and management of the combined-cycle propulsion system.

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Section: Overviewmentioning

confidence: 99%

Thermal Protection System and Thermal Management for Combined-Cycle Engine: Review and Prospects

et al. 2019

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“…They noted that the shaped holes can significantly enhance the performance of film cooling. Li et al [24,25] experimentally measured the effects of Reynolds number and blowing on a blade of the turbine. They stated that the average film cooling efficiency improved by increasing Reynolds number (at a fixed blowing ratio).…”

Section: Introductionmentioning

confidence: 99%

Film cooling modeling of a gas turbine blade by considering different injection holes with and without opening angles through CFD

Hosseini¹

2021

JMES

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One way to achieve high performance in the gas turbine is to increase the inlet temperature of the turbine. Different cooling techniques have been carried out in order to protect the turbine blades which have been exposed to such high temperatures. Film cooling as an essential cooling method needs to be enhanced to meet the challenging demand. The purpose of the present research is to analyze the film cooling performance over a NACA 0012 gas turbine blade using six different injection holes with and without opening angles, separately through Computational Fluid Dynamics (CFD). 2D Reynolds-Averaged Navier-Stokes (RANS) equations are implemented to consider the heat transfer and flow characteristics by using CFD code Ansys Fluent v16. The flow is considered as steady, turbulent, and incompressible. The RANS equation is solved with the finite-volume method for obtaining solutions. The simulation results revealed that the k-ω SST turbulence model is suitable for simulating the flow characteristics and analyzing the performance of film cooling over the blade. Also, the opening angle has a significant effect on increasing the cooling efficiency for the upper blade surface. The highest value of cooling efficiency is obtained by the injection hole with an opening angle of 15° and height of D. In this configuration, the coolant injected from hole provides better cooling coverage for the entire blade which increases the cooling effectiveness.

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“…The effect of the hot freestream Reynolds number and coolant density has been taken by Li et al [4]. They found that Abstract-The average film cooling effectiveness is numerically investigated under different conditions of Reynolds numbers and rotation speeds at the suction side of the turbine blade.…”

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confidence: 99%

“…The effect of blowing ratio (M) was taken by Li et al [4] and [7][8]. They predicted that as the blowing ratio (M) rises the average film cooling effectiveness get better.…”

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confidence: 99%

“…Rezasoltani et al [17] mentioned that as the rotation speed increases from 2400 to 3000 rpm film cooling effectiveness also increases. Li et al [4] found that the film cooling effectiveness enhances as the rotation speed increases from 400 to 700 rpm. Zhang et al [18] found that film cooling effectiveness reduces with the increase of rotation speed, while Tao et al [19] found that as the rotational speed rises the effectiveness is firstly improved and then worsened.…”

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confidence: 99%

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Investigation of Film Cooling Effectiveness under Different Reynolds Numbers and Rotation Conditions. (Dept. M)

Helw

El-Emam

Sultan

et al. 2021

MEJ. Mansoura Engineering Journal

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Film cooling characteristics on the leading edge of a rotating turbine blade with various mainstream Reynolds numbers and coolant densities

Cited by 23 publications

References 25 publications

Thermal Protection System and Thermal Management for Combined-Cycle Engine: Review and Prospects

Thermal Protection System and Thermal Management for Combined-Cycle Engine: Review and Prospects

Film cooling modeling of a gas turbine blade by considering different injection holes with and without opening angles through CFD

Investigation of Film Cooling Effectiveness under Different Reynolds Numbers and Rotation Conditions. (Dept. M)

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