Effect of Inlet Compound Angle of Backward Injection Film Cooling Hole

Jeong, Yoon Seong; Park, Jun Su

doi:10.3390/en13040808

Cited by 3 publications

(1 citation statement)

References 16 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…It was found that the critical blowing ratio is influenced by the hole shape, with a critical M of 0.75 for the expansion-shaped hole and 1.25 for the fan-shaped hole compared to critical M = 0.5 for a cylindrical hole. Jeong and Park [38] numerically assessed the effect of inlet compound angle on backward injection film cooling. Singh et al [39] performed a large eddy simulation to assess the cylindrical-hole and laid-back fan-shaped-hole film cooling with backward injection, with a fixed blowing ratio of M = 1.0 and a density ratio of DR = 2.42.…”

Section: Introductionmentioning

confidence: 99%

Numerical Investigation on Backward-Injection Film Cooling with Upstream Ramps

et al. 2022

View full text Add to dashboard Cite

The present study investigates the effects of upstream ramps on a backward-injection film cooling over a flat surface. Two ramp structures, referred to as a straight-wedge-shaped ramp (SWR) and sand-dune-shaped ramp (SDR), are considered under a series of blowing ratios ranging from M = 0.5 to M = 1.5. Regarding the backward injection, the key mechanism of upstream ramps on film cooling enhancement is suggested to be the enlargement of the horizontal scale of the separate wake vortices and the reduction of their normal dimension. When compared to the SDR, the SWR modifies the backward coolant injection well, such that a larger volume of coolant is suctioned and concentrated in the near-field region at the film-hole trailing edge. As a consequence, the SWR demonstrates a more pronounced enhancement in film cooling than the SDR in the backward-injection process, which is the opposite of the result for the forward-injection scheme. For the SWR, the backward injection provides a better film cooling effectiveness than the forward injection, regardless of blowing ratios. However, for the SDR, the backward injection could show a superior effect to the forward injection on film cooling enhancement, when the blowing ratio is beyond a critical blowing ratio. In the present SDR situation, the critical blowing ratio is identified to be M = 1.0.

show abstract

Section: Introductionmentioning

confidence: 99%

Numerical Investigation on Backward-Injection Film Cooling with Upstream Ramps

et al. 2022

View full text Add to dashboard Cite

show abstract

Numerical investigation of forward, lateral, and backward injection of the coolant fluid in various flow characteristics to find the optimum film cooling effectiveness

Kelishami

Porkhial

2023

Numerical Heat Transfer, Part A: Applications

View full text Add to dashboard Cite

Numerical Investigations of Film Cooling and Particle Impact on the Blade Leading Edge

et al. 2021

View full text Add to dashboard Cite

As a vital power propulsion device, gas turbines have been widely applied in aircraft. However, fly ash is easily ingested by turbine engines, causing blade abrasion or even film hole blockage. In this study, a three-dimensional turbine cascade model is conducted to analyze particle trajectories at the blade leading edge, under a film-cooled protection. A deposition mechanism, based on the particle sticking model and the particle detachment model, was numerically investigated in this research. Additionally, the invasion efficiency of the AGTB-B1 turbine blade cascade was investigated for the first time. The results indicate that the majority of the impact region is located at the leading edge and on the pressure side. In addition, small particles (1 m and 5 m) hardly impact the blade’s surface, and most of the impacted particles are captured by the blade. With particle size increasing, the impact efficiency increases rapidly, and this value exceeds 400% when the particle size is 50 m. Invasion efficiencies of small particles (1 m and 5 m) are almost zero, and the invasion efficiency approaches 12% when the particle size is 50 m.

show abstract

Effect of Inlet Compound Angle of Backward Injection Film Cooling Hole

Cited by 3 publications

References 16 publications

Numerical Investigation on Backward-Injection Film Cooling with Upstream Ramps

Numerical Investigation on Backward-Injection Film Cooling with Upstream Ramps

Numerical investigation of forward, lateral, and backward injection of the coolant fluid in various flow characteristics to find the optimum film cooling effectiveness

Numerical Investigations of Film Cooling and Particle Impact on the Blade Leading Edge

Contact Info

Product

Resources

About