Performance analysis of a hybrid pulse detonation engine using liquid hydrogen as fuel

Luo, Shibin; Sun, Yuhang; Song, Jeonghoon; Li, Jun

doi:10.1016/j.ijhydene.2022.04.278

Cited by 11 publications

(4 citation statements)

References 26 publications

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“…This analysis assumed that the total temperature of the turboexpander inlet T t,c can be made constant by controlling the combustion organization and the heat-exchanging area. The pressure at the heat exchanger outlet can be given by Equation (20), and the heat exchanged energy QHX can be given by Equation (21), where η HX is the heat exchange effectiveness:…”

Section: Heat Exchangermentioning

confidence: 99%

“…The NUAA-PTRE (Nanjing University of Aeronautics and Astronautics, pre-cooled turborocket engine) uses endothermic hydrocarbon and liquid oxygen as coolant to pre-burn the gas generator [19,20]. This engine can work at Mach 0∼6, and the specific impulse reaches its highest at Mach 2 and Mach 4.2, which is about 1030 s. Luo et al [21] applied the pulse detonation cycle (PDC) on the ATR and ATREX engines and proposed hybrid pulse detonation engines, which can improve the hot gas pressure, making it 1.84 and 1.96 times higher than traditional ATR and ATREX engines, respectively.…”

Section: Introductionmentioning

confidence: 99%

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Feasibility and Performance Analysis of High-Energy-Density Hydrocarbon-Fueled Turboexpander Engine

Gao,

Kang,

Sun

et al. 2023

Aerospace

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With the in-depth research on hypersonic aerodynamics and hypersonic propulsion technology, humans are growing closer to space travel. Recent studies have shown that the pre-cooled air-turborocket (ATR) or turboexpander engines are some of the potential propulsion methods for reusable space vehicles and single stage-to-orbit (SSTO) missions because they have a high specific impulse at low Mach numbers, which can overcome the problem of the “thrust gap” in turbine-based combined-cycle (TBCC) engines. The ATR engine needs an additional oxidizing agent and the turboexpander engine usually uses hydrogen as fuel, which has low energy density and poor safety. To address this problem, this paper proposed a high-energy-density (HED) hydrocarbon-fueled turboexpander engine, and its feasibility has been proven through a simplified thermodynamic model. Through detailed thermodynamic analysis based on the energy and pressure balance, this paper analyzed the performance characteristics of the engine to evaluate its capacity to work in a wide speed range at low Mach numbers. The results show that the endothermic hydrocarbon-fueled turboexpander engine has good specific impulse in Mach 0∼4 at an equivalence ratio of 0.7∼1.3, and the turboexpander engine can be combined with the dual-mode scramjet and become an efficient acceleration method for SSTO missions and the reusable spacecraft.

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Section: Heat Exchangermentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Feasibility and Performance Analysis of High-Energy-Density Hydrocarbon-Fueled Turboexpander Engine

Gao,

Kang,

Sun

et al. 2023

Aerospace

View full text Add to dashboard Cite

show abstract

“…Recent studies on pulse detonation combustion mainly focused on aero engines and rocket engines [37][38][39]; therefore, they have adopted the detonation cycle to replace the Brayton cycle to achieve high thermal efficiency and power performance. The main approach used to optimize the DDT process has been optimizing the ignition and the PDC structure.…”

Section: Introductionmentioning

confidence: 99%

Combustion Mechanism of Gasoline Detonation Tube and Coupling of Engine Turbocharging Cycle

Huang,

Wang,

Shi

et al. 2024

Energies

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Traditional exhaust-gas turbocharging exhibits hysteresis under variable working conditions. To achieve rapid-intake supercharging, this study investigates the synergistic coupling process between the detonation and diesel cycles using gasoline as fuel. A numerical simulation model is constructed to analyze the detonation characteristics of a pulse-detonation combustor (PDC), followed by experimental verification. The comprehensive process of the flame’s deflagration-to-detonation transition (DDT) and the formation of the detonation wave are discussed in detail. The airflow velocity, DDT time, and peak pressure of detonation tubes with five different blockage ratios (BR) are analyzed, with the results imported into a one-dimensional GT-POWER engine model. The results indicate that the generation of detonation waves is influenced by flame and compression wave interactions. Increasing the airflow does not shorten the DDT time, whereas increasing the BR causes the DDT time to decrease and then increase. Large BRs affect the initiation speed of detonation in the tube, while small BRs impact the DDT distance and peak pressure. Upon connection to the PDC, the transient response rate of the engine is slightly improved. These results can provide useful guidance for improving the transient response characteristics of engines.

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“…Previously, it was shown that a metamagnetic transition in an AFM compound can lead to a large positive MCE [17,18]. The magnetic transition temperature of about 27 K makes it possible to use YbCoC 2 , for example, to liquefy hydrogen, which is now actively used for various engines [19,20].…”

Section: Introductionmentioning

confidence: 99%

Some Magnetic Properties and Magnetocaloric Effects in the High-Temperature Antiferromagnet YbCoC2

et al. 2023

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The YbCoC2 compound, which crystallizes in a base-centered orthorhombic unit cell in the Amm2 space group CeNiC2 structure, is unique among Yb-based compounds due to the highest magnetic ordering temperature of TN=27 K. Magnetization measurements have made it possible to plot the H-T magnetic phase diagram and determine the magnetocaloric effect of this recently discovered high-temperature heavy-fermion compound, YbCoC2. YbCoC2 undergoes spin transformation to the spin-polarized state through a metamagnetic transition in an external magnetic field. The transition is found to be of the first order. The dependencies of magnetic entropy change ΔSm(T)—have segments with positive and negative magnetocaloric effects for ΔH≤6 T. For ΔH=9 T, the magnetocaloric effect becomes positive, with a maximum ΔSm(T) value of 4.1 J (kg K)−1 at TN and a refrigerant capacity value of 56.6 J kg−1.

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Performance analysis of a hybrid pulse detonation engine using liquid hydrogen as fuel

Cited by 11 publications

References 26 publications

Feasibility and Performance Analysis of High-Energy-Density Hydrocarbon-Fueled Turboexpander Engine

Feasibility and Performance Analysis of High-Energy-Density Hydrocarbon-Fueled Turboexpander Engine

Combustion Mechanism of Gasoline Detonation Tube and Coupling of Engine Turbocharging Cycle

Some Magnetic Properties and Magnetocaloric Effects in the High-Temperature Antiferromagnet YbCoC2

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