An integrated multidisciplinary design optimization procedure for cooled gas turbine blades

Talya, Shashishekara S.; Chattopadhyay, Aditi; Rajadas, John

doi:10.2514/6.2000-1664

Cited by 5 publications

(2 citation statements)

References 18 publications

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“…The accuracy of the pipe-network model was verified by the experimental results. Talya et al [26,27] considered the internal cooling technology and film cooling together in a turbine blade. Both the blade geometry and cooling structure were optimized.…”

Section: Introductionmentioning

confidence: 99%

A high temperature turbine blade heat transfer multilevel design platform

Wang

Luo

et al. 2020

Numerical Heat Transfer, Part A: Applications

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In this work, a fast and efficiently design method has been introduced. This design process consists of the overall design and the detailed design. For the overall design, one-dimensional pipe-network computations are employed to obtain several design cases quickly at the beginning. Meanwhile the solid domain geometry and mesh with cooling structures, i.e., film holes, impingement holes, and ribs have been generated to carry out three-dimensional (3-D) heat conduction calculations. Based on the above, a detailed design has been performed by 3-D conjugate heat transfer calculations. The results show that both the average temperature and the mass flow maximum errors between the pipe-network and 3-D conjugate heat transfer calculations are about 10%. In this article, the cooling structure of a gas turbine blade is designed with this platform. The final design results show that the maximum dimensionless temperature on the blade surface is 0.813, i.e., lower than the design requirement. The dimensionless mass flow rate in the first cooling inlet is 0.0168, and the mass flow rate in the secondary inlet is 0.0231.

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Section: Introductionmentioning

confidence: 99%

A high temperature turbine blade heat transfer multilevel design platform

Wang

Luo

et al. 2020

Numerical Heat Transfer, Part A: Applications

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“…A multidisciplinary optimization for turbine blade design was conducted by Talya et al. 12–14 The 3 D blade was divided into twelve spanwise sections. The design variables consisted of blade profile of each section, five trapezoidal shaped cooling passages and six film cooling holes.…”

Section: Introductionmentioning

confidence: 99%

Cooling structure design of gas turbine blade by using multi-level highly efficient design platform

Zhao

Luo

et al. 2020

Proceedings of the Institution of Mechanical Engineers, Part G:

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In this paper, the internal cooling structure of a second-stage rotor blade is designed by using a multi-level highly efficient design platform. The design process is divided into schematic design and detailed design in sequence. The calculations of pipe-network and heat conduction are presented to preliminary evaluate the cooling structures derived from the schematic design stage. The flow field and heat transfer characteristics of the revised cooling structures are analyzed in the detailed design by using the three-dimensional conjugated heat transfer calculation method. Topological structure, mass flow rate, pressure distribution, heat transfer coefficient and temperature distribution of the cooling channels are presented. It is found that the schematic design results based on one-dimensional to three-dimensional solution method are in good agreement with the detailed design results. Meanwile, the introduction of the schematic design is helpful to shorten the cooling design cycle and reduce the dependence of the design experience. In this work, a five-pass serpentine passage with single cooling air inlet in the cooling system may lead to low flow rate at the trailing edge, which is prone to cause hot gas back-flow and local high heat load. The cooling system with a right-angle channel and a three-pass serpentine channel helps to distribute the flow reasonably and reduce the thermal gradient on the blade surface. The optimal cooling structure meet the requirements well. Compared with the uncooled blade, the average temperature of the blade decrease over 530 K with limited cooling air.

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Integrated aerodynamic design and analysis of turbine blades

Wang

2014

Advances in Engineering Software

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An integrated multidisciplinary design optimization procedure for cooled gas turbine blades

Cited by 5 publications

References 18 publications

A high temperature turbine blade heat transfer multilevel design platform

A high temperature turbine blade heat transfer multilevel design platform

Cooling structure design of gas turbine blade by using multi-level highly efficient design platform

Integrated aerodynamic design and analysis of turbine blades

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