Thermodynamic analysis of flow field at the end of combustor simulator

Kianpour, Ehsan; Sidik, Nor Azwadi Che; Bozorg, Mohsen Agha Seyyed Mirza

doi:10.1016/j.ijheatmasstransfer.2013.02.031

Cited by 6 publications

(2 citation statements)

References 24 publications

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“…This quantity is a little bit lower compared to Colban et al [3] findings, which predicted the turbulence level between 25 and 30%. Kianpour et al [4,5] simulated the same model using -and RNG -turbulent models to solve the Navier-Stokes equation. They claimed that the RNG -turbulent model was a good choice to detect the variation of temperature in the combustor simulator.…”

Section: Introductionmentioning

confidence: 99%

The Effect of Blowing Ratio on Film Cooling Effectiveness Using Cylindrical and Row Trenched Cooling Holes with Alignment Angle of 90 Degrees

Azwadi

Kianpour

2014

Mathematical Problems in Engineering

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This paper presents the effects of blowing ratio on film cooling performance adjacent to the combustor endwall using cylindrical and row trenched cooling holes with alignment angle of 90 degrees. A three-dimensional representation of a Pratt and Whitney gas turbine engine was simulated and analysed using a commercial finite volume package FLUENT 6.2.26. The combustor simulator was designed to combine the interaction of two rows of dilution jets, which were staggered in the streamwise direction and aligned in the spanwise direction. As a result, the combustor with row trenched holes gave almost doubled cooling performance compared to the baseline case. In addition, the film cooling layer was increased at high blowing ratio, and thus it enhanced the cooling performance.

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Section: Introductionmentioning

confidence: 99%

The Effect of Blowing Ratio on Film Cooling Effectiveness Using Cylindrical and Row Trenched Cooling Holes with Alignment Angle of 90 Degrees

Azwadi

Kianpour

2014

Mathematical Problems in Engineering

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“…As stated by previous researchers [1][2][3][4][5], the famous Brayton cycle is a key to achieve higher gas turbine engine efficiency and power to weight ratio. To increase the efficiency, this thermodynamic cycle expressed that the combustor outlet temperature should increase.…”

Section: Introductionmentioning

confidence: 99%

Film-Cooling Techniques at the End of Combustor and Inlet of Turbine in a Gas Turbine Engine: A Review

Sidik

Kianpour

2014

AMM

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This study was carried out to extend database knowledge about the film cooling holes function at the end of combustor and inlet of turbine. Using the well-known Brayton cycle, rising the turbine inlet temperature, is the key to get higher engine efficiency in gas turbine engines. But the high temperature of the combustor exit flow causes non-uniformities. These non-uniformities lead to a reduction in the expected life of critical components. Therefore a cooling technique should be designed to protect these parts. There are two separate ways for Gas turbine cooling: internal cooling and external cooling. Film cooling is one of the most effective external cooling methods. In this system, a low temperature thin boundary layer such as buffer zone is formed and attached on the protected surface. In this study, a literature survey was done on the limited surveys, particularly since the first of 21th century.

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Effusion cooling characteristics of a model combustor liner at non-reacting/reacting flow conditions

Chi

et al. 2017

Applied Thermal Engineering

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Thermodynamic analysis of flow field at the end of combustor simulator

Cited by 6 publications

References 24 publications

The Effect of Blowing Ratio on Film Cooling Effectiveness Using Cylindrical and Row Trenched Cooling Holes with Alignment Angle of 90 Degrees

The Effect of Blowing Ratio on Film Cooling Effectiveness Using Cylindrical and Row Trenched Cooling Holes with Alignment Angle of 90 Degrees

Film-Cooling Techniques at the End of Combustor and Inlet of Turbine in a Gas Turbine Engine: A Review

Effusion cooling characteristics of a model combustor liner at non-reacting/reacting flow conditions

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