Multi-Row Turbomachinery Aerodynamic Design Optimization by an Efficient and Accurate Discrete Adjoint Solver
Abstract
:1. Introduction
2. Numerical Schemes and Boundary Conditions
2.1. Numerical Schemes
2.2. Boundary Conditions
3. Adjoint Principle
4. Automatic Differentiation
4.1. Forward and Backward Modes
4.2. Problem Description and Analysis
4.2.1. Conditional Branches
4.2.2. Reals/Integrals
5. Hybrid Automatic and Manual Differentiation
5.1. Strategy One: Directly Evaluate Conditional Branches
5.2. Strategy Two: Directly Evaluate Intermediate Variables
5.3. Strategy for Real-Life Adjoint Codes
6. Rotor-Stator/Stator-Rotor Interface Treatment
6.1. Mixing Plane Method
- (1)
- Average flux in the circumferential direction. It can be expressed in the following symbolic formIn Equation (11), the superscript j represents the upstream or downstream of a rotor-stator/stator-rotor interface. When j equals 1, it represents the upstream of the interface, otherwise, it represents the downstream of the interface. The subscript 0 represents the value before flux interpolation. X is the grid coordinate vector, and is the function related to flux averaging.
- (2)
- Interpolate flux in the radial direction. This step is a must as the grid distribution in the radial direction across an interface is often different as shown in Figure 8b. The interpolation operation is represented symbolically as follows
- (3)
- Update solution based upon the one-dimensional non-reflective boundary condition. This operation is represented as followsIn the above equation, the superscript ∗ represents the updated solution, and represents the function related to the solution update.
6.2. Discrete Adjoint Mixing Plane Method
- (1)
- Differentiate the subroutines related to solution update.In the above equations, and are initialized by 0.
- (2)
- Differentiate the subroutines related to flux interpolation.
- (3)
- Differentiate the subroutines related to flux averaging.In the above equations, the subscript a represents the backward mode of the AD.
7. Results
7.1. NASA Stage 35
7.1.1. Grid Independence Study
7.1.2. Adjoint Sensitivity Verification
7.1.3. Computational Efficiency
7.1.4. Results of Design Optimizations
7.2. Aachen Turbine
7.2.1. Adjoint Sensitivity Verification
7.2.2. Computational Efficiency
7.2.3. Results of Design Optimizations
8. Conclusions
- (1)
- The hybrid ADJ almost has the same sensitivity convergence histories as those from the linearized solver and higher sensitivity accuracy than the CEV. The maximum relative difference of sensitivities between the FDM and the hybrid ADJ is no more than for the cases studied in the paper.
- (2)
- The hybrid ADJ has higher computational efficiency than the discrete adjoint solver purely developed by the AD tool. About CPU time and memory consumption can be saved for the single-stage NASA Stage 35, and CPU time and memory consumption can be saved for the 1.5-stage Aachen turbine.
- (3)
- The multi-row turbomachinery aerodynamic design optimizations can be effectively performed by the hybrid ADJ. For the single-stage NASA Stage 35, the isentropic efficiency over the entire operating range of design speed is significantly improved, and the stall margin is increased for the optimized blades. For the 1.5-stage Aachen turbine, the entropy generation rate is decreased after optimization. Moreover, the variations in mass flow rate and total pressure ratio are also acceptable.
Author Contributions
Funding
Conflicts of Interest
References
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Axial | Circumferential | Radial | Total | ||
---|---|---|---|---|---|
Row 1 | Grid1 | 133 | 37 | 57 | ∼280 k |
Grid2 | 149 | 57 | 73 | ∼620 k | |
Grid3 | 161 | 85 | 89 | ∼1218 k | |
Row 2 | Grid1 | 145 | 33 | 57 | ∼273 k |
Grid2 | 161 | 49 | 61 | ∼481 k | |
Grid3 | 169 | 61 | 81 | ∼835 k |
Flow | Original ADJ | Hybrid ADJ | |
---|---|---|---|
time | 1 | 6.16 | 3.49 (−43%) |
memory | 1 | 2.52 | 2.29 (−9%) |
m(kg/s) | ||||
---|---|---|---|---|
choke | original | 21.02 | 1.745 | 83.35 |
optimized | 21.05 (+0.14%) | 1.745 (0%) | 84.00 (+0.65) | |
peak | original | 20.97 | 1.835 | 83.91 |
optimized | 21.00 (+0.14%) | 1.835 (0%) | 84.73 (+0.82) | |
stall | original | 20.60 | 1.924 | 82.19 |
optimized | 20.55 (−0.24%) | 1.922 (−0.10%) | 82.67 (+0.48) |
Flow | Original ADJ | Hybrid ADJ | |
---|---|---|---|
time | 1 | 6.16 | 3.43 (−44%) |
memory | 1 | 1.94 | 1.77 (−9.6%) |
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Wu, H.; Da, X.; Wang, D.; Huang, X. Multi-Row Turbomachinery Aerodynamic Design Optimization by an Efficient and Accurate Discrete Adjoint Solver. Aerospace 2023, 10, 106. https://doi.org/10.3390/aerospace10020106
Wu H, Da X, Wang D, Huang X. Multi-Row Turbomachinery Aerodynamic Design Optimization by an Efficient and Accurate Discrete Adjoint Solver. Aerospace. 2023; 10(2):106. https://doi.org/10.3390/aerospace10020106
Chicago/Turabian StyleWu, Hangkong, Xuanlong Da, Dingxi Wang, and Xiuquan Huang. 2023. "Multi-Row Turbomachinery Aerodynamic Design Optimization by an Efficient and Accurate Discrete Adjoint Solver" Aerospace 10, no. 2: 106. https://doi.org/10.3390/aerospace10020106
APA StyleWu, H., Da, X., Wang, D., & Huang, X. (2023). Multi-Row Turbomachinery Aerodynamic Design Optimization by an Efficient and Accurate Discrete Adjoint Solver. Aerospace, 10(2), 106. https://doi.org/10.3390/aerospace10020106