Occurrence of Rotating Detonation Waves in a Jet-Stabilized Combustor with Premixed Injection

Gejji, Rohan; Buschhagen, Timo; Slabaugh, Carson D.

doi:10.2514/1.b38292

Cited by 11 publications

(3 citation statements)

References 31 publications

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“…The tests indicated a stable operation of RDE for equivalence ratios between 0.9 and 1.2, but with detonation wave velocities less than theoretically predicted values. Gejji et al [135] used natural gas-hydrogen mixture in an axisymmetric backward-facing step combustor to produce rotating detonation combustion. The combustion instabilities that were generated in this combustor soon transitioned into rotating detonation waves with 79.9-89.7% of Chapman-Jouguet velocity.…”

Section: Effect Of Combustor Geometry On Rde Performancementioning

confidence: 99%

A Review of Pressure Gain Combustion Solutions for Aerospace Propulsion

Purushothaman

Renuke

Sorce

et al. 2022

Volume 4: Cycle Innovations; Cycle Innovations: Energy Storage

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Recent developments in Pressure Gain Combustion (PGC) technology have demonstrated its ability to achieve higher thermal efficiencies and lower carbon emissions as compared to conventional gas turbine counterpart working in Brayton cycle. Ongoing studies suggest the possibility of implementing PGC in aircraft engines by replacing the high-pressure section (HP compressor, combustion chamber and HP turbine) with a PGC system. This, coupled with research on advanced materials and cooling solutions, offers the potential for higher overall gas turbine efficiency and fuel economy, contributing towards emission reduction of the aviation sector. This paper aims at a comprehensive review of PGC technology solutions applied in the area of aero propulsion. Reported background covers the historic as well as ongoing research activities at the component level, the cycle level, and the propulsion application of Pulse Detonation Engine (PDE), Rotating Detonation Engine (RDE), Oblique Detonation Wave Engine (ODWE), Free Piston Composite Cycle Engine (FP-CCE), and wave rotor engines. The analytical, numerical, and experimental research work is reviewed, providing also a comparison of PGC engine conceptual designs with existing gas turbine engines used in aerospace propulsion.

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Section: Effect Of Combustor Geometry On Rde Performancementioning

confidence: 99%

A Review of Pressure Gain Combustion Solutions for Aerospace Propulsion

Purushothaman

Renuke

Sorce

et al. 2022

Volume 4: Cycle Innovations; Cycle Innovations: Energy Storage

View full text Add to dashboard Cite

show abstract

“…One of the leading concepts is the continuously rotating detonation engine (RDE). Many studies have been performed of various configurations, including premixed propellant injection [5], separate fuel and oxidizer injection [6], and concepts using pure oxygen or air as the oxidizer [7,8]. With each configuration comes different demands on the fueling scheme, to supply a steady and quality propellant stream to the detonation wave.…”

Section: Introductionmentioning

confidence: 99%

Computational Study of Fluidic-Valve Injectors for Detonation Engines

Small,

Zhang

2024

Aerospace

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The performance of detonation engines depends on propellant injectors. This study investigates a fluidic-valve injector mounted to a detonation tube. The injector is equipped with a recessed cavity connecting to the fuel plenum. After verifying the theoretical and numerical framework, three cases (I, II, and III) are analyzed, each representing different combinations of initial injector conditions and fuel supply setups. In all cases, a detonation wave is initiated near the headend of the detonation tube. It propagates through the initial section of the tube and undergoes diffraction and deformation at the flush-wall orifice. Among the considered cases, Case III, featuring a pre-pressurized initial injector flowfield and a total-pressure-inlet boundary, demonstrates the best agreement with the experimental results. It reveals a strong interaction between the longitudinally traveling detonation wave and the transverse propellant plume expanding from the orifice, causing the detonation wave to split. One part continues within the tube, while the other diffracts into the injector, creating a recirculation zone. Shock waves propagate within the injector and reflect at the base of the cavity, generating pressure spikes similar to the experimental observations. However, the contact surface separating the burnt products and fresh propellant reaches only a limited distance into the injector, suggesting a short interruption time and rapid recovery of the propellant supply.

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“…Yokoo et al [17] found that the combustor length did not have a great influence on the detonation wave propagation velocity and thrust performance in the hollow combustor. Recently, Gejji et al [18] achieved a premixed natural gas/air CRD in a cylindrical air-breathing engine configuration, with a CRD wave propagation speed reaching 79.9-89.7% of the CJ detonation velocity. To further simplify the air-breathing CRD engine structure and reduce the weight, a cylindrical isolator-combustor combination for the air-breathing CRD engine was proposed by Wang et al [19]; non-premixed ethylene/air CRD was realized under the inflow with Ma 2.…”

Section: Introductionmentioning

confidence: 99%

Experimental Investigation of a Cylindrical Air-Breathing Continuous Rotating Detonation Engine with Different Nozzle Throat Diameters

et al. 2022

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A continuous detonation engine with various exhaust nozzles, analogous to typical scramjet cavity combustors with variable rear-wall heights, was adopted to perform a succession of cylindrical air-breathing continuous rotating detonation experiments fueled by a non-premixed ethylene/air mixture. The results show that the detonation combustion was observed to self-sustain in the combustor through simultaneous high-speed imaging covering the combustor and isolator. A long test, lasting more than three seconds, was performed in this unique configuration, indicating that the cylindrical isolator–combustor engine exhibits potential for practical applications. Three distinct combustion modes were revealed with varied equivalent ratios (hybrid mode, sawtooth wave mode, and deflagration mode). The diameter of the nozzle throat was critical in the formation of rotating detonation waves. When the nozzle throat diameter was larger than the specific value, the detonation wave could not form and self-sustain. The upstream boundary of the shock train was supposed to be close to the isolator entrance in conditions of a high equivalence ratio and small nozzle throat diameter. In addition, it was verified that periodic high-frequency pressure oscillation could cause substantial impacts on the incoming flow as compared with the steady deflagration with the same combustor pressure.

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Occurrence of Rotating Detonation Waves in a Jet-Stabilized Combustor with Premixed Injection

Cited by 11 publications

References 31 publications

A Review of Pressure Gain Combustion Solutions for Aerospace Propulsion

A Review of Pressure Gain Combustion Solutions for Aerospace Propulsion

Computational Study of Fluidic-Valve Injectors for Detonation Engines

Experimental Investigation of a Cylindrical Air-Breathing Continuous Rotating Detonation Engine with Different Nozzle Throat Diameters

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