Numerical Study of Contoured Endwall Flow and Heat Transfer With Combustor Coolant and Film Cooling Flows for a Turbine Nozzle Guide Vane

Alqefl, Mahmood H.; Kim, Yong; Moon, Hee-Koo; Zhang, Luzeng; Simon, Terrence W.

doi:10.1615/tfec2017.cfd.018417

Cited by 1 publication

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“…[1][2][3][4] They contain also several film cooling slots to dilute the hot burned gases. 5,6 The combined effect of both swirling flames and dilution films generate high levels of turbulence and nonuniform temperature contours (known as hot-streak 7 ) at the LBC exit and the high-pressure turbine (HPT) inlet. Therefore, the nozzle guide vane (NGV) located at the interface exhibits high distorted inlet temperature.…”

Section: Introductionmentioning

confidence: 99%

Numerical prediction of heat transfer characteristics on a turbine nozzle guide vane under various combustor exit hot‐streaks

Mansouri¹

2021

Heat Trans

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The precise prediction of the aerothermal conditions at the outlet of modern combustors of aero engines is of primary interest in the aerothermal design of high‐pressure turbines. The use of high swirling flows to stabilize the flame in the new generation of lean‐burn combustors (LBCs) leads to shorter combustor length and high degrees of unsteady temperature. These aspects generate high levels of turbulence and complex temperature nonuniformity patterns at the combustor–turbine interface. Therefore, the nozzle guide vane (NGV) located at the interface exhibits a high inlet temperature gradient called a hot‐streak. The transport mechanism of the hot‐streak across the NGV needs to be decrypted to increase turbine service life and enhance its performance. In this context, the present study aims to examine numerically the effect of three new distorted hot‐streak gradients on the heat transfer characteristics across a turbine NGV. An innovative LBC is used to generate the three inlet hot‐streaks, which are highly swirled and distorted similar to real aero‐engine conditions. The use of such a generation approach avoids any simplification associated with uniform or circular contours that are widely used by researchers. A solid NGV cascade developed by NASA is adopted for the investigations. The results show significant differences in the thermal field on the cascade at each distorted thermal condition. The transport of the hot‐streak behaves differently under axial and swirl conditions. The presence of a swirl induces flow mixing and results in thermal load increasing on the cascade surfaces (NGV, hub, and shroud).

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Section: Introductionmentioning

confidence: 99%

Numerical prediction of heat transfer characteristics on a turbine nozzle guide vane under various combustor exit hot‐streaks

Mansouri¹

2021

Heat Trans

View full text Add to dashboard Cite

show abstract

Numerical Study of Contoured Endwall Flow and Heat Transfer With Combustor Coolant and Film Cooling Flows for a Turbine Nozzle Guide Vane

Cited by 1 publication

References 0 publications

Numerical prediction of heat transfer characteristics on a turbine nozzle guide vane under various combustor exit hot‐streaks

Numerical prediction of heat transfer characteristics on a turbine nozzle guide vane under various combustor exit hot‐streaks

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