Key technologies for thermodynamic cycle of precooled engines: A review

Qiuru, Zuo

doi:10.1016/j.actaastro.2020.07.039

Cited by 53 publications

(15 citation statements)

References 58 publications

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“…The mass flow rate of hydrogen is connected to the mass flow rate of helium directly by Eq. (7). Thus, if less mass of helium could achieve the same cooling effects, this would improve the fuel efficiency, because the cycle would require less mass of liquid hydrogen.…”

Section: Small Variation Analysismentioning

confidence: 99%

“…These include the turbine-based combined cycle engines (TBCC), which combine turbine engines with ramjet or scramjet technology. The rocket-based combined cycle engines (RBCC), which combine ramjet or scramjet with rocket technology, are also included (7) . Both concepts face high technical difficulties for mode conversion and thermal protection during hypersonic flight.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Multi-platform app-embedded model for hybrid air-breathing rocket-cycle engine in hypersonic atmospheric ascent

Tsentis¹,

Gkoutzamanis²,

Gaitanis³

et al. 2021

Aeronaut. j.

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This paper presents a performance analysis on a novel engine concept, currently under development, in order to achieve hybrid air-breathing rocket technology. A component-level approach has been developed to simulate the performance of the engine at Mach 5, and the thermodynamic interaction of the different working fluids has been analysed. The bypass ramjet duct has also been included in the model. This facilitates the improved evaluation of performance parameters. The impact of ram drag induced by the intake of the engine has also been demonstrated. The whole model is introduced into a multi-platform application for aeroengine simulation to make it accessible to the interested reader. Results show that the bypass duct modelling increases the overall efficiency by approximately 7%. The model calculates the specific impulse at approximately 1800 seconds, which is 4 times higher than any chemical rocket.

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Section: Small Variation Analysismentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Multi-platform app-embedded model for hybrid air-breathing rocket-cycle engine in hypersonic atmospheric ascent

Tsentis¹,

Gkoutzamanis²,

Gaitanis³

et al. 2021

Aeronaut. j.

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“…Epoxy resins (EP) are widely used in industrial blowers, aircrafts coatings, and rocket engine, due to their excellent mechanical properties, chemical stability, and corrosion resistance [1,2,3,4,5,6]. Especially in the aircraft flying speed below Mach 1.5, EP exhibit superior light weight, corrosion resistance and fatigue resistance compared to other resins [7,8,9,10,11]. Thus, in the coating on A400M and Boeing 787 aircrafts, the epoxy resin matrix accounts for 36% and 50% of the aircraft weight respectively [12].…”

Section: Introductionmentioning

confidence: 99%

Conductive Network Enhanced Carbon Black/Epoxy Composite Coating with Imide Curing for Antistatic and Heat-Resistance Improvement

Yang,

Gan,

Huang

2024

Preprint

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Epoxy resins are essential in aircraft coatings due to their strong mechanical properties and corrosion resistance. However, their limited high-temperature resistance restricts their use in high-speed aircraft, particularly for anti-static and electromagnetic-shielding coatings, which incorporate conductive networks. The dispersion of conductive fillers is hindered by the crosslink network of epoxy resins. Here, we developed a mixture curing system combining diethylenetriamine and dicarboxylic phthalimide. This system allows imide to copolymerize with the epoxy resin, enhancing temperature resistance and optimizing the dispersion of fillers by adjusting the densities of chemical and physical crosslinks. Our results indicate that the decomposition temperature of the epoxy composite increases to 383.8 °C, suitable for aircraft exceeding Mach 3 speeds. Additionally, the percolation threshold for carbon black fillers in this system is 8.1 vol%, significantly lower than the ca. 70% in volume-exclusion systems. This reduction is primarily due to the liberation of epoxy resin segments from the chemical crosslink network. The electrical performance is also notable, with volume resistivity dropping to 0.2 Ω·m near the percolation threshold, meeting anti-static product requirements. This advanced epoxy resin system shows promise for use in electromagnetic coatings on aircraft, given its enhanced temperature resistance, anti-static properties, and mechanical strength.

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“…[3][4][5] A technique pathway for raising the Mach number limit is to cool the air within a quick moment in front of the engine. 6,7 As adopted in the Synergetic Airbreath and Rock Engine (SABRE) project, a precooling cycle is used to handle the hotter and faster air flow. 8 In the pre-cooling cycle, the centrifugal compressor is a crucial component.…”

Section: Introductionmentioning

confidence: 99%

Study on alternative cycles for high-pressure low-temperature helium compressor performance experiments based on flow similarity

Liu

Song

Zhao

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part C:

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A low-temperature high-pressure helium compressor is one of the key components in a hypersonic air-breath engine cycle. Its aerodynamic performance is the basis of engine cycle design and control. The low-temperature and high-pressure conditions make it difficult in a laboratory environment to conduct a compressor performance experiment, thus constraining the engine cycle design. An alternative method is to test the compressor with other gas at a reference operation condition and then calculate the helium compressor performance according to the test results using transformation laws. This paper investigates the transformation method based on the dynamic similarity principle and derives transformation equations. CFD simulations performed on the compressors validate the equations. Eventually, the study analyzes the alternative experimental cycles.

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Key technologies for thermodynamic cycle of precooled engines: A review

Cited by 53 publications

References 58 publications

Multi-platform app-embedded model for hybrid air-breathing rocket-cycle engine in hypersonic atmospheric ascent

Multi-platform app-embedded model for hybrid air-breathing rocket-cycle engine in hypersonic atmospheric ascent

Conductive Network Enhanced Carbon Black/Epoxy Composite Coating with Imide Curing for Antistatic and Heat-Resistance Improvement

Study on alternative cycles for high-pressure low-temperature helium compressor performance experiments based on flow similarity

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