Numerical Study of the Effects of Injection Conditions on Rotating Detonation Engine Propulsive Performance
Abstract
:1. Introduction
2. Physical Model
- (a)
- if , there is no injection, and the slip wall boundary will be implemented;
- (b)
- if , the inflow velocity is locally subsonic;
- (c)
- if , the throat of the nozzle maintains choking conditions, and the injection is subsonic;
- (d)
- if , the injection is supersonic and not affected by .
3. Extension of 3D CESE Method to Cylindrical Coordinate System
4. Results and Discussion
4.1. Grid Sensitivity Analysis
4.2. Effect of Channel Width with Full Injection
4.3. Effect of Inner Radius with Fixed Injection Area
4.4. Effect of Injector Location and Size
4.5. Effect of Stagnation Pressure and Area Ratio of the Injector Nozzle
5. Conclusions
Author Contributions
Funding
Institutional Review Board Statement
Informed Consent Statement
Data Availability Statement
Conflicts of Interest
Appendix A. 3D CESE Method
Appendix A.1. Upwind CESE Method on 3D Meshes
Appendix A.2. Numerical Outline for 3D Upwind CESE Method
Appendix B. Validation of the 3D CESE Method in Cylindrical Coordinates
Appendix B.1. Sedov Blast Wave Problem
Appendix B.2. 1D Detonation Velocity
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w (mm) | p0 (atm) | (mm) | |
---|---|---|---|
1 | 10 | 0.2 | 0.5, 0.4, 0.4 |
1 | 10 | 0.2 | 0.2, 0.2, 0.2 |
1 | 10 | 0.2 | 0.1, 0.1, 0.1 |
w (mm) | (mm) | Inj Loc | (atm) | ||
---|---|---|---|---|---|
1, 3, 6, 9 | same as w | Full | 1 | 10 | 0.2 |
6 | 3 | Outer | 0.5441 | 10 | 0.2 |
9 | 3 | Outer | 0.3978 | 10 | 0.2 |
w (mm) | Inj Loc | (atm) | ||
---|---|---|---|---|
9 | 0.33∼0.75 | Outer | 10 | 0.2 |
9 | 0.33∼0.75 | Middle | 10 | 0.2 |
9 | 0.33∼0.75 | Inner | 10 | 0.2 |
w (mm) | Inj Loc | (atm) | ||
---|---|---|---|---|
9 | 0.33∼1 | Outer | 10 | 0.2 |
9 | 0.33∼1 | Outer | 20 | 0.2 |
9 | 0.33∼1 | Outer | 10 | 0.1 |
w (mm) | Isp ± SD (s) | F ± SD (N) | Vo ± SD (m/s) | Vi ± SD (m/s) |
---|---|---|---|---|
1 | 147.4 ± 0.78 | 59.7 ± 0.18 | 1975.43 ± 0.34 | 1876.66 ± 0.33 |
3 | 147.2 ± 0.38 | 169.1 ± 0.22 | 2066.44 ± 1.08 | 1756.4 ± 0.92 |
6 | 148.9 ± 0.32 | 315.5 ± 0.33 | 2374.99 ± 6.07 | 1662.4 ± 4.25 |
9 | 151 ± 0.9 | 439.7 ± 0.62 | 2960.41 ± 8.23 | 1628.23 ± 4.52 |
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Shi, L.; Fan, E.; Shen, H.; Wen, C.-Y.; Shang, S.; Hu, H. Numerical Study of the Effects of Injection Conditions on Rotating Detonation Engine Propulsive Performance. Aerospace 2023, 10, 879. https://doi.org/10.3390/aerospace10100879
Shi L, Fan E, Shen H, Wen C-Y, Shang S, Hu H. Numerical Study of the Effects of Injection Conditions on Rotating Detonation Engine Propulsive Performance. Aerospace. 2023; 10(10):879. https://doi.org/10.3390/aerospace10100879
Chicago/Turabian StyleShi, Lisong, E Fan, Hua Shen, Chih-Yung Wen, Shuai Shang, and Hongbo Hu. 2023. "Numerical Study of the Effects of Injection Conditions on Rotating Detonation Engine Propulsive Performance" Aerospace 10, no. 10: 879. https://doi.org/10.3390/aerospace10100879