A cooled turbine airfoil performance prediction method with two-dimensional CFD computation and loss models
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Xiao-Dong Zhang
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Jian-Jun Liu
Abstract
The role of turbine blade cooling and coolants are significant factors in modern gas turbine aerodynamic design. This paper presents an effective and rapid airfoil design method based on CFD computation of the S1 surface and the existing loss correlations. The method can assess the coolant mixing loss by identifying each cooling hole separately and obtain the overall mainflow aerodynamic loss for cooled airfoil. The CFD computation code of the S1 surface is powered by a two-dimensional Euler equation, which is inviscid. Typical Kacker–Okapuu empirical correlations are then used to assess the airfoil friction loss, trailing edge loss, and shock loss. A novel form of the Hartsel model for coolant mixing loss is developed and employed in the CFD codes. In the reformed model, the mixing loss coefficient is directly associated with the blowing ratio and the total pressure/temperature ratio of mainstream-to-coolant, making it more convenient than the original model in the airfoil design process. Based on a transonic turbine vane airfoil, the influences of the film outflow location and outflow Mach number on the coolant mixing loss are investigated using the above prediction method and the cascade blowing test.
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Author contributions: All the authors have accepted responsibility for the entire content of this submitted manuscript and approved submission.
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Research funding: This work was supported by National Science and Technology Major Project (No. J2019-II-0010-0030).
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Conflict of interest statement: The authors declare no conflicts of interest regarding this article.
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Artikel in diesem Heft
- Frontmatter
- Experimental and numerical study of flame structure and emissions in a micro gas turbine combustor
- Influence of innovative hydrogen multi strut injector with different spacing on cavity-based scramjet combustor
- Unsteady film cooling characteristics of the high-pressure turbine shroud with blade rotation in an aero-engine
- Probabilistic analysis of maximum mode shape for mistuned blisk
- Gain scheduling control of aero-engine based on mixing polynomial LPV synthesis
- A cooled turbine airfoil performance prediction method with two-dimensional CFD computation and loss models
- Endwall-pulsed blowing of different excitation models to control flow separation on a highly-loaded compressor cascade
- Expanding the choke margin of a mixed flow compressor stage for a micro gas turbine engine
- Supersonic jet mixing in the presence of two annular co-flow streams
- A novel design of impeller cavity pre-swirl system for efficient supercharging and low power consumption
- Detailed investigation of supersonic film cooling performance in a convergent divergent nozzle
- Numerical investigation of ice crystal melting characteristic and icing risk in an axial compressor
Artikel in diesem Heft
- Frontmatter
- Experimental and numerical study of flame structure and emissions in a micro gas turbine combustor
- Influence of innovative hydrogen multi strut injector with different spacing on cavity-based scramjet combustor
- Unsteady film cooling characteristics of the high-pressure turbine shroud with blade rotation in an aero-engine
- Probabilistic analysis of maximum mode shape for mistuned blisk
- Gain scheduling control of aero-engine based on mixing polynomial LPV synthesis
- A cooled turbine airfoil performance prediction method with two-dimensional CFD computation and loss models
- Endwall-pulsed blowing of different excitation models to control flow separation on a highly-loaded compressor cascade
- Expanding the choke margin of a mixed flow compressor stage for a micro gas turbine engine
- Supersonic jet mixing in the presence of two annular co-flow streams
- A novel design of impeller cavity pre-swirl system for efficient supercharging and low power consumption
- Detailed investigation of supersonic film cooling performance in a convergent divergent nozzle
- Numerical investigation of ice crystal melting characteristic and icing risk in an axial compressor
