Impact of Film-Cooling Jets on Turbine Aerodynamic Losses

Walters, D. Keith; Leylek, James H.

doi:10.1115/1.1303818

Cited by 43 publications

(9 citation statements)

References 25 publications

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“…Table 5 reports on the interaction of the outgoing coolant from holes and cutback with the mainstream in terms of momentum flux ratio I . In several papers, I was addressed as the correct parameter for comparing film cooling studies with varying DR, from an aerodynamic 30,31 and thermal 32 point of view. In short, the scaling of the overall aerodynamic/thermal field with I is far better than with VR .…”

Section: Resultsmentioning

confidence: 99%

Adiabatic and conjugate simulations on the flow field in a gas turbine vane with pressure side film cooling and trailing edge cutback

Ravelli

Barigozzi

2014

Proceedings of the Institution of Mechanical Engineers, Part A:

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The present study concentrates on the numerical investigation of pressure side film cooling in a linear nozzle vane cascade typical of a high-pressure turbine in gas turbine engines. The cooling scheme features a pressure side cutback and two rows of cooling holes located upstream of the cutback. The main goal is to evaluate the applicability of a simple numerical method, i.e. the steady incompressible Reynolds-averaged Navier Stokes, in such a complex industrial application. The simulations are performed according to an adiabatic and conjugate approach. Two values of the coolant-to-mainstream mass flow ratio ( MFR = 1% and 2.8%) are simulated at exit Mach number of M2 is = 0.2. The computed flow/temperature fields in the cooled regions of the vane pressure side are presented and compared to available measurements of: holes and cutback exit velocity and discharge behavior; boundary layer along traverses at strategic axial locations, adiabatic film cooling effectiveness. In addition, distributions of overall film cooling effectiveness and heat transfer coefficients are reported for the conjugate cases. Both adiabatic and conjugate techniques provide reasonable predictions of three-dimensional aerodynamic and thermal features of the investigated cooled vane. The conjugate heat transfer is much more complicated than one-dimensional conduction within the vane material.

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Section: Resultsmentioning

confidence: 99%

Adiabatic and conjugate simulations on the flow field in a gas turbine vane with pressure side film cooling and trailing edge cutback

Ravelli

Barigozzi

2014

Proceedings of the Institution of Mechanical Engineers, Part A:

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“…Multiple numerical studies have been conducted to understand the film cooling physics under a steady main flow. Walters and Leylek (2000) used RAMPANT code [5] to simulate film cooling on a flat plate [6]. They used the standard k-ε of Launder and Spalding for a 3-D unstructured mesh.…”

Section: Introductionmentioning

confidence: 99%

Large Eddy Simulation of Film Cooling with Bulk Flow Pulsation: Comparative Study of LES and RANS

Baek¹,

Ahn²

2020

Applied Sciences

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The effects of bulk flow pulsations on film cooling in gas turbine blades were investigated by conducting large eddy simulation (LES) and Reynolds-averaged Navier–Stokes simulation (RANS). The film cooling flow fields under 32 Hz pulsation in the mainstream from a cylindrical hole inclined 35° to a flat plate at the average blowing ratio of M = 0.5 were numerically simulated. The LES results were compared to the experimental data of Seo, Lee, and Ligrani (1998) and Jung, Lee, and Ligrani (2001). The credibility of the LES results relative to the experimental data was demonstrated through a comparison of the time-averaged adiabatic film cooling effectiveness, time- and phase-averaged temperature contours, Q-criterion contours, time-averaged velocity profiles, and time- and phase-averaged Urms profiles with the corresponding RANS results. The adiabatic film cooling effectiveness predicted using LES agreed well with the experimental data, whereas RANS highly overpredicted the centerline effectiveness. RANS could not properly predict the injectant topology change in the streamwise normal plane, but LES reproduced it properly. In the case of the injectant trajectory, which greatly influences film cooling effectiveness, RANS could not properly predict the changes in the streamwise velocity peak due to flow pulsation, but they were predicted well with LES. RANS greatly underpredicted the streamwise velocity fluctuations, which determine the mixing of main flow and injectant, whereas LES prediction was close to the experimental data.

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“…Walters et al. 20 conducted the computational study of the aerodynamic impact of film cooling on a linear turbine cascade using a high-quality hybrid mesh comprising hexahedrons, tetrahedrons, prisms, and pyramids. The results indicated that the computational method can predict film cooling losses accurately.…”

Section: Introductionmentioning

confidence: 99%

“…[16][17][18][19] However, the computational investigation based on the hybrid mesh only attracts little attention on the study of film cooling injection. Walters et al 20 conducted the computational study of the aerodynamic impact of film cooling on a linear turbine cascade using a high-quality hybrid mesh comprising hexahedrons, tetrahedrons, prisms, and pyramids. The results indicated that the computational method can predict film cooling losses accurately.…”

Section: Introductionmentioning

confidence: 99%

Computational study of compound angle film cooling flow field and aerodynamic losses using a parallel hybrid mesh Navier–Stokes code

Luo

Misaka

Obayashi

et al. 2015

Proceedings of the Institution of Mechanical Engineers, Part A:

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Flow characteristics and aerodynamic losses of film cooling injection with compound angles of 30°, 60°, and 90° for velocity ratios of 0.5, 1.0, and 2.0 are numerically investigated using the high-quality hybrid meshes comprising tetrahedrons, prisms, and pyramids. The solutions are obtained by solving the compressible Reynolds-averaged Navier–Stokes equations, and the cell-vertex finite volume method is used to discretize these equations. The predicted results are firstly validated against the experimental data. It has been found that the variation tendency of mass average net total pressure loss coefficient with compound angles is reasonably predicted and in many cases well predicted. The analyses based on net total pressure losses show that the aerodynamic losses tend to increase with the increasing of compound angle regardless of the velocity ratio, and the tendency becomes more obvious when the velocity ratio is large. On the other hand, some typical cases are additionally calculated with different turbulence models and flux computation schemes for the comparisons. A latest proposed numerical flux computation method, simple low-dissipative AUSM (SLAU) scheme, is adopted in the predictions. The results indicate that SLAU scheme is slightly superior to Harten–Lax–van Leer–Einfeldt–Wada scheme in the prediction of compound angle film cooling injection.

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Impact of Film-Cooling Jets on Turbine Aerodynamic Losses

Cited by 43 publications

References 25 publications

Adiabatic and conjugate simulations on the flow field in a gas turbine vane with pressure side film cooling and trailing edge cutback

Adiabatic and conjugate simulations on the flow field in a gas turbine vane with pressure side film cooling and trailing edge cutback

Large Eddy Simulation of Film Cooling with Bulk Flow Pulsation: Comparative Study of LES and RANS

Computational study of compound angle film cooling flow field and aerodynamic losses using a parallel hybrid mesh Navier–Stokes code

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