CH* Luminance Distribution Application and a One-Dimensional Model of the Supersonic Combustor Heat Release Quantization
-
Z. P. Wang
,
L. W. Cheng
Abstract
One-dimensional model is an important way to evaluate the performance and flow characteristics of dual-mode scramjet combustor. Current work is based on a modified one-dimensional model assisted by measurements acquired on a direct-connected scramjet facility. CH* images and gas-sampling facility have been employed to quantify heat release for optimizing one-dimensional model. The results show that modified one-dimensional model gives a better evaluation of axis parameters distribution, especially for Mach number, which is the standard parameter to evaluate combustion mode. The ram/scram mode derived by the analytical results has been investigated. Intensive heat release is beneficial to obtain more stable pre-combustion shock and subsonic flow in the recirculation zone.
Funding statement: The project is sponsored by the National Natural Science Foundation of China (11272323). Author thanks Qian Daxing, Li Fei, Li Qiang.
Nomenclature
- m
Mass flow rate (kg/s)
- P
Static pressure (N/m2)
- T
Static temperature (K)
- Cp
Specific heat at constant pressure (J/(kg*K))
- q
Heat release (J)
- A
Core-area of combustor flow (m3/s)
- M
One-dimensional Mach number
- ρ
One-dimensional density (kg/m3)
- ϒ
One-dimensional specific heat ratio
- h
Enthalpy of flow (J)
- L
Luminosity intensity of combustor
- X
Volume fraction
Subscript
- t
Stagnation value
- w
Wall value
- total
Total value
- average
Average molecular weight
- in
Conditions at the entry of isolator
- out
Conditions at the exit of combustor
- local
Local value of the gas
References
1. Ferri A. Review of problems in application of supersonic combustion. J R Aeronaut Soc 1964;645(68):575–97.10.1017/S0368393100080391Search in Google Scholar
2. Heiser WH, Pratt DT, Deley DH. Hypersonic airbreathing propulsion. Washington, DC: American Institute of Aeronautics and Astronautics Inc., 1994.10.2514/4.470356Search in Google Scholar
3. Bussing TRA, Murman EM. A one-dimensional unsteady model of dual-mode scramjet operation. AIAA Paper, 83–0422.Search in Google Scholar
4. Chang P, Yu G. The study of one-dimensional flow analysis model of the combustor in supersonic combustion experiments. Exp Meas Fluid Mech 2003;17(1):88–82.Search in Google Scholar
5. Cristian B, Con JD. Quasi-one-dimensional model of hydrogen-fueled scramjet combustors. J Propul Power 2009;25(6):1220–25.10.2514/1.43716Search in Google Scholar
6. Starkey RP, Lewis MJ. Quasi-one-dimensional high-speed engine model with finite-rate chemistry. J Propul Power 2001;17(6):1366–74.10.2514/2.5889Search in Google Scholar
7. Price RB, Hule IR, Sugden TM. Optical studies of the generation of noise in turbulent flames. Proc Comb Inst 1968;12:1093–102.10.1016/S0082-0784(69)80487-XSearch in Google Scholar
8. Najm HN, Paul PH, Mueller CJ, Wycokoff PS. On the adequacy of certain experimental observables as measurements of flame burning rate. Combust Flame 1998;113:312–32.10.1016/S0010-2180(97)00209-5Search in Google Scholar
9. Micka DJ, Driscoll JF. Combustion characteristics of a dual-mode scramjet combustor with cavity flameholder. Proc Combust Inst 2009;32(2):2397–404.10.1016/j.proci.2008.06.192Search in Google Scholar
10. Fotia ML, Driscoll JF. Ram-scram transition and flame/shock-train interactions in a model scramjet experiment. J Propul Power 2012;29(1):261–73.10.2514/1.B34486Search in Google Scholar
11. Cheng L, Zhong F, Gu H, Zhang X. Application of conjugate gradient method for estimation of the wall heat flux of a supersonic combustor. Int J Heat Mass Transfer 2016;96:249–55.10.1016/j.ijheatmasstransfer.2016.01.036Search in Google Scholar
12. Wang ZP, Li F, Gu HB, Yu XL, Zhang XY. Experimental study on the effect of combustor configuration on the performance of dual-mode combustor. Aerosp Sci Technol 2015;42:169–75.10.1016/j.ast.2015.01.008Search in Google Scholar
© 2019 Walter de Gruyter GmbH, Berlin/Boston
Articles in the same Issue
- Frontmatter
- Original Research Articles
- Optimization Design and Experimental Study of a Two-disk Rotor System Based on Multi-Island Genetic Algorithm
- Experimental Investigation of the Effect of the Probe Support Tail Structure on the Compressor Cascade Flow Field
- Investigation on Rotor-Labyrinth Seal System with Variable Rotating speed
- Numerical Prediction of Impact of Clearance on Rotordynamic Coefficients for Labyrinth Brush Seal
- CH* Luminance Distribution Application and a One-Dimensional Model of the Supersonic Combustor Heat Release Quantization
- Bleeding Control for Improving Internal Waverider Inlet Self-Starting ability
- Soot Formation and Its Effect in an Aero Gas Turbine Combustor
- Studies on the Effect of Staggering the Rear Rotor in a Counter Rotating Turbine with Respect to Flow and Performance Parameters
- Aerodynamic Performance and Flow Characteristics of an Industrial Centrifugal Blower Volute with Varied Cross-Sectional Shapes/Area Ratios
- CFD Design Study of a Pressure Probe for Centerline Static Pressure Measurement in Supersonic Ejectors
- The Performance of the Self-Supplying Vortex Generator Jets on a High-Speed Compressor Cascade
Articles in the same Issue
- Frontmatter
- Original Research Articles
- Optimization Design and Experimental Study of a Two-disk Rotor System Based on Multi-Island Genetic Algorithm
- Experimental Investigation of the Effect of the Probe Support Tail Structure on the Compressor Cascade Flow Field
- Investigation on Rotor-Labyrinth Seal System with Variable Rotating speed
- Numerical Prediction of Impact of Clearance on Rotordynamic Coefficients for Labyrinth Brush Seal
- CH* Luminance Distribution Application and a One-Dimensional Model of the Supersonic Combustor Heat Release Quantization
- Bleeding Control for Improving Internal Waverider Inlet Self-Starting ability
- Soot Formation and Its Effect in an Aero Gas Turbine Combustor
- Studies on the Effect of Staggering the Rear Rotor in a Counter Rotating Turbine with Respect to Flow and Performance Parameters
- Aerodynamic Performance and Flow Characteristics of an Industrial Centrifugal Blower Volute with Varied Cross-Sectional Shapes/Area Ratios
- CFD Design Study of a Pressure Probe for Centerline Static Pressure Measurement in Supersonic Ejectors
- The Performance of the Self-Supplying Vortex Generator Jets on a High-Speed Compressor Cascade
