Ultra-Compact Combustion Technology Using High Swirl for Enhanced Burning Rate

Zelina, Joseph; J.Ehret,; Hancock, Robert D.; Roquemore, W. M.; Shouse, Dale T.; Sturgess, G. J.

doi:10.2514/6.2002-3725

Cited by 35 publications

(11 citation statements)

References 6 publications

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“…A tetrahedral mesh is used with a maximum cell dimension of 0.3 mm. A standard k-ε model is used for turbulence, for its good compromise between computing economy and accuracy, as well as its good agreement with experiments under high centrifugal field for the ultra-compact combustor [22]. Turbulence model parameters are set to default values and inlet turbulence intensity is set to 5 %.…”

Section: B Numerical Simulationmentioning

confidence: 99%

High-g Field Combustor of a Rim-Rotor Rotary Ramjet Engine

Rancourt¹,

Picard²,

Plante³

et al. 2014

50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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High-g field combustion such as in rotary ramjet engines is a promising approach to reduce nitride oxides and combustor size by taking advantage of the flame acceleration due to the buoyancy of the products over the reactants. This paper presents a high-g field combustor design for a rim-rotor rotary ramjet engine. In this device, a premixed flow of air and fuel is ignited in the non-rotating inlet track and then swallowed and stabilized in the rotating combustion chamber. Outboard ignition frees the rotating structure from igniters, increasing the maximal tangential speed of the engine and thus its maximal efficiency. The rotating combustor design benefits from extreme centrifugal fields (10 5 to 10 7 g's) for both stabilizing the flame during ignition and maximize flame velocity. A simple buoyancy-driven combustion model allows estimating the combustor length and shows good agreement with numerical simulations, which demonstrate a combustion efficiency to be higher than 85%, even with some reactants bypassing the flameholder. Experiments demonstrate ignition at tangential speeds from 250 to 380 m/s, combustion efficiency from 60 to 75 % up to a centrifugal acceleration of 7×10 5 g, and positive indicated power.

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Section: B Numerical Simulationmentioning

confidence: 99%

High-g Field Combustor of a Rim-Rotor Rotary Ramjet Engine

Rancourt¹,

Picard²,

Plante³

et al. 2014

50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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“…Several swirl air valve settings were investigated during the course of the combustor checkout testing. AFRL studies 9 indicate an optimum swirl air mass fraction of approximately 20% of the axial flow. Furthermore, a centrifugal loading of Fr = 3000 or higher was suggested for stable combustion * , where Fr is the Froude number defined as…”

Section: B Flowfield Measurementsmentioning

confidence: 99%

“…While the AFRL combustor 9 uses a separate swirl air supply with controllable pressure, for simplicity the CJES combustor makes use of an inlet flow conditioner screen (Dynapore High Flow Media HFM 600). The flow conditioner screen provides backpressure in a core air plenum and passive control of the amount of swirl air entering the swirl cavity as shown in Fig.…”

Section: B Flowfield Measurementsmentioning

confidence: 99%

Acoustic Characterization of Compact Jet Engine Simulator Units

Doty

Haskin

2013

19th AIAA/CEAS Aeroacoustics Conference

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“…One is that a combustion chamber is arranged in the high and low pressure turbine transition section of the channel, the other one is that UCC scheme, which adopts the addition of a circumferential cavity through around the low pressure turbine vane, for combustion of fuel mixed with air [4][5][6]. Mawid M A promoted the mixing of gas and mainstream in the circumferential cavity by setting a radial vane cavity (RVC) on the UCC guide vanes [7,8].…”

Section: Introductionmentioning

confidence: 99%

Numerical Simulation of an Ultra-compact Interstage Turbine Burner with Increasing Number of Cavities in the Cavity

Guang-qi¹,

Guan²,

Chang³

et al. 2017

dtcse

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Abstract. The Interstage Turbine Burner (ITB) engine provide significantly higher specific thrust with no or only small increases in thrust specific fuel consumption substitute for conventional gas engine with after-burners. Continue combustion between a high pressure turbine stage and low pressure turbine stage is organized. Ultra-Compact Combustor (UCC), which is one of mainstream design concepts of ITB, has a broad application prospect in the field of aviation with the advantages of compact structure and high combustion efficiency. In order to improve the application of Ultra-Compact Turbine interstage combustor in aero-engine, the numerical simulation was carried out by using CFD technique to research on the influence of the number of cavities in the cavity on the ITB. The results show that the increasing number of structures of cavities in the cavity will enhance the circumferential cavity of the fuel and air mixing and burning, promote the combustion mixture to the mainstream radial transport capacity and improve combustion efficiency and uniformity of exit temperature field.

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Ultra-Compact Combustion Technology Using High Swirl for Enhanced Burning Rate

Cited by 35 publications

References 6 publications

High-g Field Combustor of a Rim-Rotor Rotary Ramjet Engine

High-g Field Combustor of a Rim-Rotor Rotary Ramjet Engine

Acoustic Characterization of Compact Jet Engine Simulator Units

Numerical Simulation of an Ultra-compact Interstage Turbine Burner with Increasing Number of Cavities in the Cavity

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