Flow and Cooling Characteristics of Gas Turbine Film Cooling According to Forward and Backward Injection

Jeong, Yoon Seong; Jung, Kuk Jin; Park, Jun Su

doi:10.5293/kfma.2017.20.5.013

Cited by 1 publication

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“…Although the film cooling effectiveness of backward injection film cooling was higher than that of forward injection film cooling, the backward flow of combustion gas from the cooling hole outlet during backward injection was observed [16]. If the combustion gas flows backward into cooling holes, then the film cooling efficiency drops, and stress accumulates inside the cooling holes.…”

Section: Introductionmentioning

confidence: 95%

Effect of Inlet Compound Angle of Backward Injection Film Cooling Hole

Jeong

Park

2020

Energies

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Backward injection film cooling holes were studied to improve film cooling effectiveness using simple cylindrical holes, and this principle was applied to an actual gas turbine. Although film cooling effectiveness was improved using a backward injection film cooling hole, the backward flow of combustion gas from the backward injection cooling hole was one of the major reasons for cracks in the hot components. To prevent cracks and backward flow in the backward injection film cooling hole, this study changed the inlet compound angle of the backward injection film cooling hole. Numerical analysis using CFX v. 17.0 was performed to calculate the flow characteristics and film cooling effectiveness of backward injection film cooling. Aa a result, the effect of the inlet compound angle of the backward injection film cooling hole was confirmed to prevent the backward flow, which increased upon increasing the inlet compound angle. This study shows that the backward flow and cracks in the backward injection film cooling hole can be prevented simply by changing the inlet compound angle.

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Section: Introductionmentioning

confidence: 95%