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Visualization method of Clearance Design of Gas Turbine using Commercial Finite Element Analysis program

상용 유한요소 해석 프로그램을 이용한 가스터빈 간극 설계의 가시화 방법

  • Han, Do Won (GT System Integration Team, Doosan Heavy Industries & construction) ;
  • Kim, Yeong Chun (GT System Integration Team, Doosan Heavy Industries & construction) ;
  • Kim, Kyung Chun (School of Mechanical Engineering, Pusan National University)
  • Received : 2019.04.11
  • Accepted : 2019.04.29
  • Published : 2019.04.30

Abstract

A gas turbine is the main equipment of a power plant that generates electricity by high-speed rotation of the rotor in a high-temperature environment. In particular, in the case of medium to large-sized gas turbines, the rotor is composed of a plurality of stages, and each component is exposed to different physical environments. Especially, in the case of the tip clearance of the turbine, it is a very important factor in the performance of the design items and the operation of the stable turbine, and a design considering the physical behavior of all major parts should be done. In this study, we will discuss the process of visualizing the physical behavior of turbine operating conditions and the method of designing tip clearance for stable operation by using commercial finite element analysis program for gas turbine assembly model and single product.

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Fig. 1. Configuration of industrial gas turbine

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Fig. 2. Convection coefficient change of main flow path and bearing housing.

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Fig. 3. Convection Temperature change of main flow path and bearing housing.

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Fig. 4. Applied thermal boundary condition for heat transfer analysis.

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Fig. 5. Concept of consideration of mechanical load.

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Fig. 6. Analysis process for clearance design.

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Fig. 7. 2D Rotor FEM model for transient thermal-structural analysis.

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Fig. 8. 3D Stationary parts FEM model for transient thermal-structural analysis.

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Fig. 9. 3D blade and vane FEM model for transient thermal-structural analysis.

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Fig. 10. Temperature contour result of stationary parts.

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Fig. 11. Displacement contour result of Stationary parts

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Fig. 12. Temperature contour result of blade

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Fig. 13. Displacement contour result of blade

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Fig. 14. Temperature contour result of rotor

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Fig. 15. Displacement contour result of rotor

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Fig. 16. Calculation concept of interaction of axial and radial displacement.

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Fig. 17. Calculation concept of radial displacement of stationary parts.

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Fig. 18. Time history displacement result from shutdown to full speed full load condition.

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Fig. 19. Clearance design concept.

Acknowledgement

Supported by : 한국에너지기술평가원(KETEP)

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