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Research Papers

Research on a Transonic Supercritical Carbon Dioxide Centrifugal Turbine

[+] Author and Article Information
Zehai Yang, Dan Luo

School of Energy and Power Engineering,
University of Shanghai for Science
and Technology,
Shanghai 200093, China

Diangui Huang

School of Energy and Power Engineering,
University of Shanghai for Science
and Technology,
Shanghai 200093, China
e-mail: dghuang@usst.edu.cn

1Corresponding author.

Manuscript received August 13, 2018; final manuscript received March 18, 2019; published online July 19, 2019. Assoc. Editor: Jinliang Xu.

ASME J of Nuclear Rad Sci 5(4), 041202 (Jul 19, 2019) (10 pages) Paper No: NERS-18-1072; doi: 10.1115/1.4043295 History: Received August 13, 2018; Revised March 18, 2019

Recently, the supercritical carbon dioxide Brayton (SCO2) cycle gained a lot of attention for its application to next-generation nuclear reactors. Turbine is the key component of the energy conversion in the thermodynamic cycle. Transonic centrifugal turbine has advantages of compatibility of aerodynamic and geometric, low cost, high power density, and high efficiency; therefore, it has opportunity to become the main energy conversion equipment in the future. In this paper, a transonic nozzle and its corresponding rotor cascade of the single-stage centrifugal turbine were designed. In addition, the three-dimensional (3D) numerical simulation and performance analysis were conducted. The numerical simulation results show that the predicted flow field is as expected and the aerodynamic parameters are in good agreement with one-dimensional (1D) design. Meanwhile, the off-design performance analysis shows that the transonic centrifugal turbine stage has wide stable operation range and strong load adaptability. Therefore, it can be concluded that the proposed turbine blade has good performance characteristics.

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Figures

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Fig. 1

Basic SCO2 Brayton cycle system

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Fig. 2

Structure schematic diagram of centrifugal turbine

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Fig. 3

Enthalpy–entropy diagram of the single stage turbine

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Fig. 4

Velocity triangle of the centrifugal turbine stage

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Fig. 5

Process flow chart for forward problem design method

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Fig. 6

Section of transonic nozzle flow channel

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Fig. 7

Tangent angles of mean line and thickness distributions for the rotor blade

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Fig. 8

Optimized rotor blade profile

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Fig. 9

Three-dimensional geometry of the stator and the rotor

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Fig. 10

Computational domain detailed sections of the structured mesh near the wall: (a) computational domain, (b) detailed sections of the nozzle, and (c) detailed sections of the rotor

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Fig. 11

Streamline at 50% span

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Fig. 12

Contour of temperature at 50% span

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Fig. 13

Contour of static pressure at 50% span

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Fig. 14

Contour of Mach number at 50% span

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Fig. 15

Static pressure distribution along nozzle blade surface at different spans

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Fig. 16

Variation of the total-to-static efficiency with pressure radio at different speeds

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Fig. 17

streamline at midspan under 5000 rpm and 7000 rpm at the respective optimal pressure ratio: (a) 5000 rpm and (b) 7000 rpm

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Fig. 18

Variation of the mass flow rate with pressure radio at different speeds

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Fig. 19

Variation of the output power with pressure radio at different speeds

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