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Investigation on One-Dimensional Loss Models for Predicting Performance of Multistage Centrifugal Compressors in Supercritical CO2 Brayton Cycle

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Abstract

The main compressor in a supercritical carbon dioxide (SCO2) Brayton cycle works near the critical point where the physical properties of CO2 are far away from the ideal gas. To investigate the effectiveness of the conventional one-dimensional (1D) loss models for predicting the performance of compressors working in such nontraditional conditions, detailed comparisons of 1D predicted performance, experimental data and three-dimensional CFD results are made. A 1D analysis method with enthalpy and total pressure based loss system is developed for multistage SCO2 centrifugal compressors, and it is firstly validated against the experimental results of a single stage SCO2 centrifugal compressor from the Sandia National Laboratory. A good agreement of pressure ratios with experiments can be achieved by the 1D method. But the efficiency deviations reveal the potential deficiencies of the parasitic loss models. On the basis of the validation, a two-stage SCO2 centrifugal compressor is employed to do the evaluation. Three-dimensional CFD simulations are performed. Detailed comparisons are made between the CFD and the 1D results at different stations located in the compressor. The features of the deviations are analyzed in detail, as well as the reasons that might cause these deviations.

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Abbreviations

A :

passage area

B :

fractional area blockage

b :

hub-to-shroud passage width

C fdf :

disk torque coefficient

c :

absolute velocity

c̄ :

mean absolute velocity

c f :

skin friction coefficient

D f :

diffusion factor

d :

diameter

d H :

hydraulic diameter

h :

enthalpy

Δh :

enthalpy loss

Δh Euler :

impeller blade work

I blade :

impeller blade work input coefficient

L b :

length of blade mean camberline

m :

meridional coordinate

ṁ :

mass flow

N :

rotating speed

P :

pressure

r :

radius

SNL:

Sandia National Laboratory

T :

temperature

u :

Circumferential speed

w :

relative velocity

w̄ :

mean relative velocity

X :

judgment criterion for the sonic condition

Z :

effective number of blades

α:

absolute flow angle from meridional

β :

blade angle from meridional

ε :

average size of the blade gap from impeller inlet to outlet

εw :

wake fraction of the blade-to-blade space at impeller outlet

η :

adiabatic efficiency

ξ :

enthalpy loss coefficient

ϖ :

total pressure loss coefficient

ϖ inc0 :

minimum incidence loss coefficient

ρ :

fluid density cslip slip velocity at impeller outlet σ slip factor

ϕ :

flow coefficient

0:

total thermodynamic condition or stage inlet

1:

impeller blade inlet

2:

impeller outlet

3:

vaned diffuser inlet

4:

vaned diffuser outlet

6:

crossover inlet

7:

return channel vane trailing edge

cl :

clearance gap

DIF :

vaned diffuser

h :

hub

i :

station number

is :

isentropic

m :

meridional component

RC :

return channel

t :

tip

th :

throat

u :

tangential component

*:

condition at minimum loss incidence angle

’:

value relative to rotating frame of reference

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Acknowledgements

This work was supported by the National Key Research and Development Program of China (No. 2016YFB0600100), National Natural Science Foundation of China (No. 51506195), and the Collaborative Innovation Center of Major Machine Manufacturing in Liaoning.

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Authors and Affiliations

  1. School of Energy and Power Engineering, Dalian University of Technology, Dalian, 116024, China

    Wenyang Shao, Jinguang Yang, Xiaofang Wang & Guochuan Lyu

  2. Institute of Engineering Thermophysics, Chinese Academy of Sciences, Beijing, 100190, China

    Juan Du

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  1. Wenyang Shao
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Correspondence to Jinguang Yang.

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Shao, W., Du, J., Yang, J. et al. Investigation on One-Dimensional Loss Models for Predicting Performance of Multistage Centrifugal Compressors in Supercritical CO2 Brayton Cycle. J. Therm. Sci. 30, 133–148 (2021). https://doi.org/10.1007/s11630-020-1242-1

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