Combustion behaviors of GO2/GH2 swirl-coaxial injector using non-intrusive optical diagnostics

Cai, Guobiao; Zhang, Yang; Yu, Nanjia

doi:10.1016/j.actaastro.2016.03.033

Cited by 21 publications

(5 citation statements)

References 30 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The temperature dependence of each excitation line is expressed as fB/T when the collisional quenching rate is assumed as cP, where fB is the Boltzmann fraction, T is the temperature, c is a constant and P is the pressure. The fB for diatomic molecules such as OH, which has linear molecular geometry, is defined in the existing literature (Bechtel, 1979, GuoBiao et al, 2016. The variation of fB/T for the Q1(9.5) transition in the given temperature range is approximately 17% at maximum.…”

Section: Experimental Facility and Configurationmentioning

confidence: 99%

OH planar laser-induced fluorescence measurement for H2/O2 jet diffusion flames in rocket combustion condition up to 7.0 MPa

Higuchi

Takeuchi

Nunome

et al. 2019

JTST

View full text Add to dashboard Cite

OH planar laser-induced fluorescence measurement for H 2 /O 2 jet diffusion flames in rocket combustion condition up to 7.0 MPa Abstract This study focuses on the application of OH planar laser-induced fluorescence (OH-PLIF) in high-pressure rocket combustion conditions, up to 7.0 MPa. The signal to noise ratio of PLIF degrades in high-pressure combustion owing to effects such as line broadening and interference from intense chemiluminescence. The OH(2,0) band excitation method was applied to obtain the OH(2,1) fluorescence emitted near 290 nm and filter out the intense OH(0,0) band chemiluminescence emitted near 308 nm. The gaseous H2/O2 (GH2/GO2) jet diffusion flame was formed using a recessed coaxial shear injector. The GH2/GO2 injection Reynolds number, Re (ReH2/ReO2 ≈ 2320/22800-4660/45600), was varied to examine the variation of the flame structure and reaction zone thickness under each pressure condition Pc, and Re injection condition. In addition, the variation of the experimentally derived full width at half maximum (FWHM) of the radial OH distribution, OH, with the Damköehler number, Da, was compared with that of the simulated FWHM of the OH mole fraction, OH-SIM. The OH distribution was clearly observed in the instantaneous PLIF image while eliminating the intense OH chemiluminescence even in the highest pressure condition of 7.0 MPa, which is a pressure higher than any of the previous OH-PLIF studies conducted on rocket combustion. The flame structure showed the typical characteristics of a turbulent jet diffusion flame and depended on Re rather than on the chamber pressure Pc. The variation of OH with Da corresponded qualitatively with OH-SIM and showed the characteristics of flame stretch in the vicinity of the injector.

show abstract

Section: Experimental Facility and Configurationmentioning

confidence: 99%

OH planar laser-induced fluorescence measurement for H2/O2 jet diffusion flames in rocket combustion condition up to 7.0 MPa

Higuchi

Takeuchi

Nunome

et al. 2019

JTST

View full text Add to dashboard Cite

show abstract

“…In general, N 2 H 4 can be used as both fuel of bipropellant thrusters and propellants of monopropellant attitude control thrusters. Compared with the traditional chemical propulsion system, DMPS integrates the high reliability, low thrust and favorable impulse performance of the monopropellant and the high specific impulse of the bipropellant, which makes the space propulsion system have higher overall performance [8][9][10].…”

Section: Introductionmentioning

confidence: 99%

A dual-mode hydrogen peroxide and kerosene space propulsion system pressurized by electric pumps

Zhou

et al. 2022

J. Phys.: Conf. Ser.

View full text Add to dashboard Cite

In this study, the performance characteristics and previous application cases of the dual-mode propulsion system (DMPS) were discussed. Besides, a dual-mode hydrogen peroxide and kerosene space propulsion system pressurized by electric pumps was proposed via the analysis of the existing problems with respect to the dual-mode propulsion system. In addition, the working process of this system was analyzed by system modeling and simulation. Further, the feasibility of DMPS was verified by exploring the working characteristics of the bipropellant main thruster and the monopropellant attitude control thruster. As per the analysis results, the DMPS proposed in this study contributed to eliminating the problems in the application of the dual-mode propulsion system at the present stage, and it also provided effective guidance in improving the performance of the propulsion system, adjusting the thrust flow rate, and making the propellant non-toxic.

show abstract

“…Wang et al reported that the flame was anchored in the center nozzle tip of the gas-centered swirl coaxial injector and further enhanced in the conical region downstream using the large eddy method. Guobiao et al studied the effect of the ratio of the oxidizer mass flow rate to the fuel rate on the flame structure of swirl coaxial injectors using the OH-PLIF technology and high-speed photography. It was shown that the flame of swirl coaxial injectors forms a recirculation zone at the central axis, which causes the return of a large amount of combustion products, and that the combustion zone mainly concentrates in the spray shear layer.…”

Section: Introductionmentioning

confidence: 99%

Experimental Study on the Unsteady Spray Combustion Process of a Liquid Oxygen/Methane Swirl Coaxial Injector

Cao

Bai

et al. 2021

ACS Omega

View full text Add to dashboard Cite

The present study experimentally investigated the dynamic spray combustion process of a liquid-centered swirl coaxial injector using liquid oxygen/ methane in an optically accessible liquid rocket engine. Data were obtained at combustor pressures from 0.4 to 1.8 MPa and the ratio of the oxidizer mass flow rate to the fuel rate between 1.32 and 1.55. Liquid oxygen was injected at 120 K, and the injection temperature of gaseous methane was about 285 K. Based on the obtained spatial distribution and oscillation characteristics of liquid oxygen/ methane flame, the combustion process was described by four subprocesses: ignition, low-frequency oscillation combustion, quasi-steady state combustion, and shutdown. In the quasi-steady state combustion subprocess, both the flame length and the normalized flame area are the largest, and the flame expansion angle is the smallest. At the initial stage of combustion, the instability of the liquid oxygen phase state leads to flame instability, which generates low-frequency unstable combustion with a dominant frequency of 93.74 Hz. In addition, the highfrequency (2500−3000 Hz) oscillation of the flame appeared in the whole combustion process. It has been confirmed to be caused by the self-pulsation of spray. Furthermore, with the increase in liquid oxygen manifold pressure, the liquid oxygen phase state changes from a two-phase mixture of liquid and gaseous oxygen to a liquid phase, which increases the mass flow rate of liquid oxygen entering into the combustor, thus generating the increase in the high oscillation frequency of the flame through the whole combustion process.

show abstract

Combustion behaviors of GO2/GH2 swirl-coaxial injector using non-intrusive optical diagnostics

Cited by 21 publications

References 30 publications

OH planar laser-induced fluorescence measurement for H<sub>2</sub>/O<sub>2</sub> jet diffusion flames in rocket combustion condition up to 7.0 MPa

OH planar laser-induced fluorescence measurement for H<sub>2</sub>/O<sub>2</sub> jet diffusion flames in rocket combustion condition up to 7.0 MPa

A dual-mode hydrogen peroxide and kerosene space propulsion system pressurized by electric pumps

Experimental Study on the Unsteady Spray Combustion Process of a Liquid Oxygen/Methane Swirl Coaxial Injector

Contact Info

Product

Resources

About