Advantages of a full-flow staged combustion cycle engine system

Davis, Jason; Campbell, Robert L.

doi:10.2514/6.1997-3318

Cited by 19 publications

(7 citation statements)

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“…The parameters in Table 3 indicate that the limiting conditions of the scaling criterion are satisfied. The values of Re for the oxygen jets in the three conditions range from 8×10 5 to 5.3×10 6 , and those for the hydrogen jets range from 2.26×10 5 to 1.5×10 6 . The flows are also treated as in the turbulent states.…”

Section: Pressure Scalingmentioning

confidence: 92%

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Scaling of the flowfield in a combustion chamber with a gas–gas injector

2010

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The scaling of the flowfield in a gas-gas combustion chamber is investigated theoretically, numerically and experimentally. To obtain the scaling criterion of the gas-gas combustion flowfield, formulation analysis of the threedimensional (3D) Navier-Stokes equations for a gaseous multi-component mixing reaction flow is conducted and dimensional analysis on the gas-gas combustion phenomena is also carried out. The criterion implies that the size and the pressure of the gas-gas combustion chamber can be changed. Based on the criterion, multi-element injector chambers with different geometric sizes and at different chamber pressures ranging from 3 MPa to 20 MPa are numerically simulated. A multi-element injector chamber is designed and hot-fire tested at five chamber pressures from 1.64 MPa to 3.68 MPa. Wall temperature measurements are used to understand the similarity of combustion flowfields in the tests. The results have verified the similarities between combustion flowfields under different chamber pressures and geometries, with the criterion applied.

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Section: Pressure Scalingmentioning

confidence: 92%

“…[3−5] The full flow stage combustion (FFSC) cycle engine is preferable because of its high performance and high reliability. [6] Gas-gas combustion technology is a key technology for this kind of engine. Although a lot of studies have been carried out until now, [7−19] the scaling of gas-gas combustion is, unfortunately, not involved.…”

Section: Introductionmentioning

confidence: 99%

Scaling of the flowfield in a combustion chamber with a gas–gas injector

2010

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“…V.C.2, which is not positive toward this engine cycle. In support of the X-33 and Reusable Launch Vehicle programs, an engine system designated the RS-2100 was developed, 40 using the full-ow cycle as shown in Fig. 3.…”

Section: Additional Enginesmentioning

confidence: 99%

Cycles for Earth-to-Orbit Propulsion

Manski¹,

Goertz²,

Sa-oslash³

et al. 1998

Journal of Propulsion and Power

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The reduction of Earth-to-orbit launch costs in conjunction with an increase in launcher reliability and operational ef ciency are the key demands on future space transportation systems. Results of various system analyses indicate that these demands can be met with future single-stage-to-orbit (SSTO) vehicles using advanced technologies for both structure and propulsion systems. This paper will provide a classi cation and description of all turbopump feed liquid rocket engine cycles, followed by a combined vehicle/propulsion analysis of the design parameters for the propulsion systems and their associated thermodynamic cycles for the launch of future SSTO vehicles. Existing and projected rocket engine cycles capable of SSTO missions will be presented.

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“…With the rapid development of human space activities, the nontoxicity spacecraft propellants has become an inevitable trend. At present, hydrogen is regarded as an ideal propellant fuels for spacecraft engines due to its easy ignition and non-polluting products [1,2]. However, hydrogen has a very low boiling point and low density in the case of liquid hydrogen, which in turn leads to an increase in the fuel reserve space required for the aircraft and a reduction in flight payload [3].…”

Section: Introductionmentioning

confidence: 99%

Characterization of the effects of a plasma injector driven by AC dielectric barrier discharge on ethylene-air diffusion flame structure

Zheng¹,

Nie

Zhou

et al. 2020

Open Physics

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AbstractA dielectric barrier discharge plasma controlled diffusion flame experimental system was built based on the designed coaxial swirling plasma injector. The air plasma was generated within the annulus gap of the injector by alternating current dielectric barrier discharge. The discharge characteristics and power of plasma injector under different actuation intensities and air flowrates were measured. Through the measurement techniques, such as schlieren imaging, broadband chemiluminescence image and CH* chemiluminescence, the effect and mechanism of plasma on ethylene-air normal diffusive jet and flame was explored. The results showed that a large number of filamentary discharge channels are formed in air plasma. The increase of air flowrates weakened the intensity of discharge to a certain extent. The induced jet generated by the plasma can short the laminar length of the ethylene-air jet, accelerate the transition of the flow jet, enhance the turbulence and the mixing of the fuel and the oxidizer. The higher the actuation intensity, the shorter distance of the cold jet transition zone, the higher the jet turbulence. Depending on the aerodynamic and kinetic effects, plasma can improve the stability of ethylene-air diffusive flame and reduce the lift height between the flame root and injector. The plasma can also expand the flammability limit of ethylene-air flame and make the flame ignited under some conditions that could not be. In addition, the CH* chemiluminescence shows that, in a certain range of discharge voltage, the heat release distribution can be changed on both sides of the flame, and its representative length are generally reduced as the voltage rises. On the contrary, the overtop voltage could lead to a decrease of flame heat release.

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Advantages of a full-flow staged combustion cycle engine system

Cited by 19 publications

References 0 publications

Scaling of the flowfield in a combustion chamber with a gas–gas injector

Scaling of the flowfield in a combustion chamber with a gas–gas injector

Cycles for Earth-to-Orbit Propulsion

Characterization of the effects of a plasma injector driven by AC dielectric barrier discharge on ethylene-air diffusion flame structure

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