1. Introduction
The Brayton cycle with supercritical carbon dioxide (s-CO
2) as a working fluid has raised universal attention in the last few decades [
1]. The s-CO
2 Brayton cycle exhibits a few advantages compared with the Brayton cycle with the working fluid. A higher cycle thermal efficiency can be achieved with a relatively lower turbine inlet temperature, which could enhance the operation’s dependability, reduce the system’s complexity and save on costs. Furthermore, the lower turbine inlet temperature of the s-CO
2 Brayton cycle makes the applications possible in solar energy and geothermal power generation, waste heat recovery, and nuclear power generation [
2,
3,
4,
5,
6]. Moreover, because it is an environmentally friendly working fluid, no pollution is generated in the power generation process of the s-CO
2 Brayton cycle. However, more challenges bring to the key power generation component, i.e., the s-CO
2 radial inflow turbine design, resulting from unique thermal-physical properties. The geometry scaling effect is a salient issue that needs to be resolved due to the smaller geometry of the s-CO
2 turbine [
7]. Hence, the radial inflow design with high efficiency is a fundamental issue for applying the advanced s-CO
2 Brayton cycle.
Sandia National Laboratory [
8] performed the pioneering experimental work to test the s-CO
2 Brayton cycle and key component performance. In their work, the No. 2 radial inflow turbine was designed with a power of 213 kW and a total-to-static efficiency of 87%. Bechtel Marine Propulsion Corporation [
9] designed the s-CO
2 radial inflow turbine with a total inlet temperature of 299 °C. However, due to several confines in their experimental test, the turbine inlet’s total temperature was limited to 232 °C, and the rotating speed could not achieve the nominal value. In the experimental test carried out by the Tokyo Institute of Technology [
10], the rotating speed of the s-CO
2 radial inflow was only 55,000 rpm, which was much lower than the design value of 100,000 rpm; this was attributed to the technical limitations of the shaft bearing and sealing. Hence, the output power and the efficiency measured were lower than the designed values. The experimental tests performed by the Korea Institute of Energy Research [
11] found the same astriction. The designed rotating speed of their s-CO
2 radial inflow turbine was 70,000 rpm; however, the actual experimental value was limited to 30,000 rpm.
Zhou et al. [
12] designed the s-CO
2 radial inflow turbine with the power of 1.5 MW and performed the performance prediction based on the Computational Fluid Dynamics (CFD) method using the software package ANSYS CFX. They found that the predicted total-to-static efficiency is 83.49%, with a deviation less than 5% from the calculated value from their one-dimensional design code. Lv et al. [
13] presented an optimization work for the one-dimensional design of the s-CO
2 radial turbine based on the Sequential Quadratic Programming (SQP) optimization algorithm. They revealed the superiority of the optimization work with an improvement of 2.27% on the total-to-static efficiency. Saeed et al. [
14] designed s-CO
2 turbines using deep neural networks. Results suggest that the employed multifaceted approach reduces computational time and resources significantly and is required to completely understand the effects of various turbine design parameters on its performance and sizing. Lee et al. [
15] developed a code to predict the aerodynamic performance of an s-CO
2 radial inflow turbine under the off-design working condition. The variations were less than 10% between the one-dimensional calculations and the three-dimensional CFD predictions. The energy loss empirical or semi-empirical correlations determine the predicted accuracy. However, limited correlations are available, especially for the s-CO
2 radial inflow turbine. Persky and Sauret [
16] evaluated the analytical energy loss correlations used in the preliminary design for the air or gas radial inflow turbine in designing the s-CO
2 turbine. They found that the published loss model configurations may not suit off-design analysis for the s-CO
2 radial inflow turbine. They developed a new loss model configuration with less than a 2% difference in efficiency prediction over the CFD result. With the aid of the CFD method, Keep and Jahn [
17] studied the loss contribution for a 300 kW low specific speed s-CO
2 radial inflow turbine. Their results concluded that the end-wall viscous losses in the stator are dominated, which plays a more significant role than that for the gas radial inflow turbine. Yang et al. [
18] focused on the leakage loss in the impeller backface cavity for the s-CO
2 radial inflow turbine and revealed the relevance of the leakage loss to the labyrinth seal geometrical parameter.
The present paper provides an optimization design platform based on the one-dimensional design method in Shu et al. [
19] to carry forward the efficient s-CO
2 radial inflow turbine design. An in-house code is developed in MATLAB language. The design variables are selected with nozzle velocity coefficient, rotor velocity coefficient, reaction degree, diameter ratio, absolute flow angle rotor inlet, and relative flow angle at the rotor outlet. The optimization function maximizes the total-to-static efficiency with aerodynamic and structural constraints. The build-in function,
fmincon, is treated as the optimization algorithm. The optimization code is then applied to design the s-CO
2 radial inflow turbine with a power of 2.1 MW. The comparison of the total-to-static efficiency is performed between the CFD simulation and the one-dimensional calculation under the design working condition to validate the current code. The flow field and the performance are also analyzed in detail under the off-design working conditions.
2. One-Dimensional Optimization Design
The general flow chart of the current one-dimensional optimization design for the s-CO
2 radial inflow turbine is shown in
Figure 1. The optimization target, the design variables and the relevant lower and upper limits, the initial values of the design variables, and the restricted conditions are required to be specified to run the optimization work. The built-in function in MATLAB,
fmincon, is selected as the optimization algorithm. Because the
fmincon function is optimized locally, the predicted optimization result strongly relies on the given starting value. Hence, the final optimization result is obtained by adjusting the initial values and the trial. When the optimization value in the current step is equal to or larger than that in the former step, the optimization process is completed. In the one-dimensional design method for the s-CO
2 radial inflow turbine, the calculated value of the total-to-static efficiency also depends on the thermo-physical properties of the s-CO
2, the selection of the energy loss models, and the specific constrained conditions.
2.1. Thermo-Physical Property Calculation
Unlike conventional air or gas, working fluid s-CO
2 should be treated as the real working fluid with varying thermo-physical properties. In the current code, the thermo-physical properties are acquired from a featured software package NIST REFPROP [
20]. Hence, the thermodynamic parameter at the nozzle inlet, rotor inlet, and rotor exit and the total-to-static efficiency of the s-CO
2 radial inflow turbine can be accurately calculated.
2.2. Optimization Algorithm
The optimization algorithm is the fundamental part of an optimization issue, determining the local or global way and the optimization time. The optimization function,
fmincon, is commonly applied in constrained nonlinear multivariable nonlinear system optimization problems [
21]. The option SQP is chosen for the algorithm option. The Hessian matrix is updated using the BFGS algorithm in the quadratic programming problem. Its major advantages include succinct code, simple usage, and fewer iterations. The comparison test for the current one-dimensional optimization design showed that the iteration steps are 36, much lower than the iteration step of 120 for the Simulated Annealing Approach. The confinement factor is that only the local optimum result can be acquired, which may differ from the optimum global result. In the present study, the initialized variables are carefully given using the screening method [
22] for the radial inflow turbine design. Furthermore, the additional iterative process shown in
Figure 1 is applied to pursue the global optimum solution.
2.3. One-Dimensional Design Method
The total-to-static efficiency
ηs can be calculated by considering several energy losses, which is given by:
where
ηu is the peripheral efficiency,
ζf is the disk friction energy loss coefficient,
ηΔ is the clearance efficiency,
ζi is the incidence loss coefficient,
ηe is the partial admission efficiency.
From the energy standpoint, the peripheral efficiency
ηu is calculated by:
where
ζn,
ζr, and
ζc2 are the energy loss coefficients in the nozzle, rotor blade, and the leaving velocity at rotor exit.
The peripheral efficiency
ηu can also be expressed by the design variables as follow:
where
xa is the velocity ratio,
φ and
ψ are the nozzle velocity coefficient and rotor blade velocity ratio,
α1 is the absolute flow angle at rotor inlet,
β2 is the relative flow angle at rotor exit, Ω is the reaction degree,
is wheel diameter ratio. The definitions of
xa,
φ,
ψ, and
can be referred to in [
19].
The disk friction loss coefficient
ζf is given by:
where
G is the mass flow rate, Δ
hs is the turbine isentropic enthalpy drop,
f is the coefficient with a constant value of 4,
ρ1,
D1, and
u1 are the density, diameter, and peripheral velocity at the rotor inlet.
The expression of clearance efficiency
ηΔ is as follows:
where Δ
r is the radial clearance between the shroud and the casing,
lm is the arithmetic mean blade height.
The current radial inflow design assumes the full admission pattern and the partial admission efficiency ηe equals 1.
The incidence loss
ζi is additionally considered in the current study, which is given by:
where
w1 is the relative velocity and relative flow angle at the rotor inlet,
i1 is the incidence angle at the rotor inlet. The definition of
i1 is as follows:
where
β1b is the rotor inlet blade angle of 90°,
β1 is the relative flow angle at the rotor inlet.
2.4. Design Constraints and Optimization Function
As seen in the one-dimensional design method, seven design parameters influence the final total-to-static efficiency of the radial inflow turbine. The upper and lower limits of each design parameter for the current design are listed in
Table 1, following the suggested values in [
19]. Note that the design parameters vary within a wide region, providing sufficient wide design space for the following optimization.
The aerodynamic limitations and structural constraints must be considered for the one-dimensional optimization design. In the current study, the followings constraints are covered and listed in
Table 2. The incidence angle limitation avoids severe reverse flow and the excessive incidence loss at the rotor inlet. The point of the Mach number constraint is to prevent the energy loss and the secondary flow loss from the shock wave. The absolute flow angle at the rotor exit is bounded from 85° to 95°, which guarantees the close axial flow direction for the working fluid at the rotor exit to avoid excessive leaving velocity energy loss. The meridional passage geometry depends on the specific values of the relative shroud diameter and the hub diameter. Hence, the current constraints are assumed to avoid excessive expansion in the meridional passage. When the relative blade height is smaller than its lower limit, the blade height may be too small, especially for the s-CO
2 radial inflow turbine with a heavy working fluid. However, the relative blade height with a large value would influence the shape of the meridional passage.
Under the consideration of the constraints mentioned above, the optimization function is given as follows:
The fmincon function is to find the minimum. When the minimum of 1/ηs is achieved, the maximum of ηs is obtained equivalently. Hence, the reciprocal of ηs is supposed to be the optimization function.
2.5. Optimization Result
A design case is performed to validate the current in-house one-dimensional optimization design code. The design specifications of the s-CO
2 radial inflow turbine are listed in
Table 3.
In the optimization process, the numbers of nozzle and rotor blades are fixed as constant values of 33 and 19, respectively. The one-dimensional design results originated from the initial design parameters, and the optimization results are listed in
Table 4. It is seen that the optimal set of the seven design variables results in a large rotor geometry and a slightly higher specific speed than the initial design. The optimal design provides an output power of 2.118 MW and a total-to-static efficiency of 85.30%.
3. Numerical Methodology and Setup
The steady-state, three-dimensional Navier-Stokes equations are solved using the commercial software NUMECA. The turbulence model comparison work for the radial inflow turbine in [
23] concluded that the Spalart-Allmaras turbulence model was a suitable choice with good convergence and adaptability. Hence, the Spalart-Allmaras turbulence model is selected for the turbulent closure in the current study.
The three-dimensional model is generated based on the one-dimensional optimization design geometry, as shown in
Figure 2. In the current simulation, one nozzle passage and the rotor blade passage are selected as the computational domain to save the computational cost. The structured meshes are generated using IGG-AutoGrid5, shown in
Figure 3. The O4H and HI topology structures are applied for the mesh generation in the nozzle passage and the rotor blade passage. The meshes around the endwall, nozzle, and rotor blade surfaces are refined with an expansion ratio of 1.2 to describe the velocity boundary layers. The computational meshes stratify the numerical simulation standards with an orthogonality angle of less than 20°, an aspect ratio of less than 2500, and an extension ratio of less than 2.
A grid independence test is performed to verify the accuracy of the numerical results.
Figure 4 shows the total-to-static efficiency variation at five computation mesh resolutions. It is observed that the value of total-to-static efficiency is nearly unchanged since the mesh resolution is higher than 1.72 million. Hence, the mesh resolution of 1.72 million is adopted for the following simulations to balance the prediction accuracy and computation time. The mesh resolutions for the nozzle passage and rotor blade passages are 0.89 million and 0.83 million, respectively.
Alireza et al. [
24] pointed out that the thermal-physical properties of the s-CO
2 significantly impact the prediction accuracy for the performance and flow field of the radial inflow turbine. Hence, the real gas thermal-physical properties are generated using a built-in code, TabGen, in the software NUMECA. Because the table generation technique is adopted in the code TabGen, table resolution must be determined in advance. Based on the design specifications for the radial inflow turbine listed in
Table 3, the pressure ranges from 5 MPa to 30 MPa, and the temperature ranges from 400 K to 1000 K for the table generation. Note that the thermal-physical properties follow the perfect gas law with explicit functions, which change successively depending on the temperature and pressure at a specific thermodynamic state of CO
2. It is seen in
Table 5 that the perfect gas thermal-physical properties lead to a deviation of nearly 3% less in the total-to-static efficiency than the real gas ones. Combatively, only a deviation of 0.01% occurs among different table resolutions. Therefore, the table resolution of 201 × 201 is adopted in the following simulations.
However, the thermal-physical properties with a high resolution degrade the computation stability; hence, a low value of the CFL number is required to improve the stability. The CFL number is set as 0.5 in the trade-off between the computation time and stability for the current simulations.
The boundary conditions in simulations are set up as follows. The total pressure and temperature are imposed at the nozzle inlet, and static pressure is set at the rotor exit. The domain of the nozzle passage is stationary, and the domain of the rotor blade passage is rotational. The boundary conditions can be seen in
Table 3 for the simulation of the design working conditions. For the simulations under off-design working conditions, the static pressure at the rotor exit varies to achieve the given total-to-static expansion ratio, and the rotational speed differs. The wall surfaces at the hub, blade, and shroud are assumed to be adiabatic, smooth, and in no-slip condition. When the root means square residuals of all variables are lower than 10–6, and the variation of mass flow rate entering into the nozzle passage is less than 0.5%, the convergence of the CFD simulation is achieved.