Design Optimization Methods for Improving HPT Vane Pressure Side Cooling Properties Using Genetic Algorithms and Efficient CFD

Johnson, Jamie J.; King, Paul I.; Clark, John P.; Ooten, Michael K.; Afb, Wright-Patterson

doi:10.2514/6.2012-326

Cited by 9 publications

(3 citation statements)

References 24 publications

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“…(8) are further added in the continuity, momentum, and energy equations in eqs. (1) and (3). The mass-flow rate, mjet, volume of injection region, Vol jet, velocity, ujet,I, and internal energy, ejet, associated with the jet stream need to be specified prior to simulations:…”

Section: Tip Injection Modelingmentioning

confidence: 99%

“…With the development in computer technologies and numerical algorithms, CFD has become an indispensable tool to evaluate gas turbine aero-thermal performance. Moreover, CFD-based optimization plays a crucial role in turbine design systems [1]. Various CFD methods have been proposed in the literature to model the flow and heat transfer in gas turbines.…”

Section: Introductionmentioning

confidence: 99%

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Numerical simulations and optimizations for turbine-related configurations

2020

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In order to accelerate the numerical simulation and optimization of gas turbine-related configurations, a source based computational fluid dynamics (SCFD) approach is developed for flow and heat transfer simulations. Different sources depending on the fluid porosity at each grid node in the computational domain are introduced to the continuity, momentum, energy and turbulence model equations, so that both the fluid and solid regions can be solved as one region. In the present paper, test cases including a ribbed channel and a winglet shrouded turbine cascade with tip injection are investigated using the SCFD and CFD with body-fitted meshes. Impacts of grid clustering and turbulence model equation sources on the SCFD precision are examined. Numerical results show that the SCFD predicts consistent aerothermal performance with the fluid dynamics with body-fitted meshes and experiments. The validated SCFD scheme is then employed in a response surface optimization of tip jet holes on the winglet shroud tip. A jet arrangement with the minimum energy loss and injection mass-flow rate is obtained, indicating that source based predictions can be applied to the preliminary aero-thermal design of turbine blades.

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Section: Tip Injection Modelingmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Numerical simulations and optimizations for turbine-related configurations

2020

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show abstract

“…A lot of researches have been carried out to study the effect of geometrical parameters, for example the diameter, location or shape of the film cooling holes, on the blade cooling to obtain key parameters and design rules [ [3] , [4] , [5] , [6] , [7] ]. Johnson et al [ 8 , 9 ] carried out the optimization of the hole shape on the cooling effectiveness of nozzle guide vane. In their studies, a transpiration boundary condition is used for modeling film cooling injection, and the near wall temperature is selected as the objective function.…”

Section: Introductionmentioning

confidence: 99%