Ram and Ejector-Jet Modes Experiments of the Combined Cycle Engine in Mach 4 Flight Conditions

Tani, Kazuo; Izumikawa, Muneo; Saito, Toshihito; Ono, Fumiei; Murakami, Atsuo

doi:10.2514/6.2008-103

Cited by 12 publications

(9 citation statements)

References 5 publications

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“…The attained airflow static pressure at M4 condition was 0.68 q 1 , close to the measured value 3) of 0.60 q 1 . The airflow should be mixed with the rocket exhaust plume, and instantaneous and complete mixing was assumed at the entrance of the combustor section.…”

Section: Engine Internal Flow Simulationmentioning

confidence: 48%

“…Details will be found in Ref. 3. The entrance area of the scramjet flow-pass was 0.22 m in width and .020 m in height.…”

Section: Engine Model Configurationmentioning

confidence: 99%

“…To attain one-dimensional airflow state at the entrance of the combustor section, an equilibrium calculation was carried out with an kinetic energy efficiency based on an empirical equation 5) and estimated capture ratio 3) shown in Table 1. The attained airflow static pressure at M4 condition was 0.68 q 1 , close to the measured value 3) of 0.60 q 1 .…”

Section: Engine Internal Flow Simulationmentioning

confidence: 99%

“…A constant area section was attached to the downstream of the diverging combustor to ensure the thermal choking in this section, so that acceleration of the flow (accompanying reduction in pressure) due to thermal choking would not reduce the pressure thrust on the thrust surface of the diverging section. This configuration was expected to deliver a very high thrust, however, the engine model testing 3) showed that fuel injection at further upstream location (i.e., within the diverging section) produced a higher thrust level than the designed injection.…”

Section: Introductionmentioning

confidence: 99%

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Dual-mode Operation of a Rocket-Ramjet Combined Cycle Engine

Tomioka

Tani

Masumoto³

et al. 2010

AEROSPACE TECHNOLOGY JAPAN

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One-dimensional evaluation of Ramjet-mode operation was carried out on a rocket-ramjet combined cycle engine model. For simplicity, instantaneous mixing between the airflow and rocket exhaust, instantaneous heat release, and pressure recovery by a normal-shock wave were assumed. Shock wave location was so decided that the heat release at the injection (heat addition) location was to thermally-choke the combustion gas flow. By changing the injection location, it was shown that a further downstream injection resulted in a further thrust production and a further fuel flow rate requirement for choking, and a lesser specific impulse. Balancing the thrust production and the specific impulse in terms of the launch vehicle acceleration performance should be pursued. The total pressure loss within the engine model was dominated by the shock wave location, not depended on injection location and fuel flow rate, so that having shock wave penetration to further upstream location was beneficial both for thrust production in the engine and at the external nozzle.

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Section: Engine Internal Flow Simulationmentioning

confidence: 48%

“…Details will be found in Ref. 3. The entrance area of the scramjet flow-pass was 0.22 m in width and .020 m in height.…”

Section: Engine Model Configurationmentioning

confidence: 99%

Section: Engine Internal Flow Simulationmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Dual-mode Operation of a Rocket-Ramjet Combined Cycle Engine

Tomioka

Tani

Masumoto³

et al. 2010

AEROSPACE TECHNOLOGY JAPAN

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“…9 The model was tested under the ejector-jet mode at a sea-level, static-air condition (M0 condition) and was tested under the ramjet and ejector-jet modes at a Mach 4 flight condition at the Ramjet Engine Test Facility. 10,11 Figures 5 and 6 show pictures of the model at the M0 and the M4 condition tests. Operations of the ejector-jet and ramjet modes were demonstrated.…”

Section: Rocket-ramjet Combined-cycle Engine Studiesmentioning

confidence: 99%

Research Activities of Advanced Propulsion Technology in JAXA

Kanda¹

2009

Trans. JSASS Space Tech. Japan

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The rocket-ramjet combined-cycle engine is studied for the next space transportation in JAXA. The engine realizes a higher effective specific impulse than that of the conventional rocket engines. Engine model combustion tests were conducted at in the ejector-jet mode at a sea-level static-air condition and in the ramjet mode at a Mach 4 flight condition, and are planed in the scramjet mode at Mach 6. Flight tests with the CAMUI rocket are planed for the ejector-jet system design technology. Aerodynamic tests and combustor tests are conducted to modify the engine design technologies. Studies on the high enthalpy flow and light weight material are also conducted.

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