Evaluation of Metallic-tube-cooled C/C Composite Structure by Rocket Combustor

Takegoshi, Masao; Ono, Fumiei; Ueda, Shuichi; Saito, Toshihito; Hayasaka, Osamu

doi:10.2514/6.2007-2357

Cited by 2 publications

(4 citation statements)

References 3 publications

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“…According to predictions at a temperature of 3000 K (equivalent wall temperature of 1973 K and wall heat flux of 4.6 MW/m 2 ), this structure has the ability to maintain the surface temperature below 2000 K. [14][15] Based on the study above, another cooling structure combining C/C composites and the metal tube was evaluated in a rocket combustor. [16] A cylindrical C/C composite structural segment with an inner diameter of 50 mm and a length of 72 mm was designed for this experiment. A 2D layup along the axial direction of the flow path was chosen for the C/C composite to improve the thermal conductivity.…”

Section: Thermal Protection Performance Of Carbon Fiber-reinforced Co...mentioning

confidence: 99%

“…Experiment results show that a regenerative cooling structure combining composite materials and metal cooling channels have great potential for development in high thermal load environments. [16] Snecma Propulsion Solide (SPS) worked with NASA and Pratt & Whitney to design and fabricate an all-C/SiC composite heat transfer structure. [17] This solution applied two [15] C/SiC composite panels.…”

Section: Thermal Protection Performance Of Carbon Fiber-reinforced Co...mentioning

confidence: 99%

“…carbon-reinforced composites, such as the low material tensile strength, high brittleness, and low thermal conductivity, the combined cooling structures adopting the metal channels and composites are often used in practical applications. [11][12][13][14][15][16][17][18][19][20][21][22][23] However, increasing the proportion of carbon-reinforced composites with lower density, higher specific strength and higher temperature resistance in active thermal protection structures has become the trend. The complex physicochemical processes, such as the heat transfer deterioration and enhancement, [24][25][26] heat transfer instability, [27][28] flow maldistribution, [29][30] thermal oxidative coking [31][32] and, pyrolytic coking problems, [33][34][35][36] etc., are still not clear in the composite regenerative cooling channel.…”

Section: Introductionmentioning

confidence: 99%

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Application of Carbon Fiber‐Reinforced Ceramic Composites in Active Thermal Protection of Advanced Propulsion Systems: A Review

Jing

Xin

Zhang

et al. 2023

The Chemical Record

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Thermal protection is one of the crucial issues for the advanced propulsion systems of Reusable Launch Vehicles. New service requirements for materials, such as high strength, low density, low thermal expansion, high thermal stability, etc., are raised for the thermal structure with the increasing demand of flight Mach numbers and thrust‐to‐weight ratio. Carbon fiber‐reinforced ceramic composites, which generally meet the aforementioned requirements, show great potential for various applications and they have been widely applied in the thermal protection for hypersonic vehicles. This paper gives a comprehensive and systematic review of current research status for carbon fiber‐reinforced ceramic composites applied in the thermal structure of advanced propulsion systems. Three aspects are presented and discussed: the ceramic composites fabrication and the property characterization, the thermal performance of composite thermal structure used in practical engines, and the numerical methods for predicting mechanical and thermal properties of composites as well as the physicochemical phenomenon in the cooling channels. Firstly, the main manufacturing processes for the carbon‐reinforced ceramic composites are presented and the corresponding advantages and disadvantages are analyzed. The high‐temperature oxidation and ablation behaviors of composites are demonstrated and the improvement of oxidation and ablation resistance by introducing the ultra‐high‐temperature ceramics into C/C composites is discussed in detail. Then, several typical applications of carbon fiber‐reinforced ceramic composites (mainly C/SiC), including the work of RCI, JAXA and NASA, have been reviewed and analyzed. After that, the current research status of macroscale equivalent and multiscale numerical methods for predicting the mechanical and thermal properties of composites as well as the complex physicochemical phenomenon occurring in hydrocarbon fuels are sorted out. Finally, several potential prospects are pointed out for the future research on the thermal protection of advanced propulsion systems based on the carbon fiber‐reinforced ceramic composites.

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Section: Thermal Protection Performance Of Carbon Fiber-reinforced Co...mentioning

confidence: 99%

Section: Thermal Protection Performance Of Carbon Fiber-reinforced Co...mentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Application of Carbon Fiber‐Reinforced Ceramic Composites in Active Thermal Protection of Advanced Propulsion Systems: A Review

Jing

Xin

Zhang

et al. 2023

The Chemical Record

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“…Thus, the material itself should be cooled to control the surface temperature. As the composite material itself cannot be used as pressurized cooling channel, metal tubes should be pressed upon the composite material to transfer heat to the coolant [15].…”

Section: A For Cooling Requirement Reductionmentioning

confidence: 99%

R&D on Hydrocarbon-fueled RBCC Engines for a TSTO Launch Vehicle

Ueda

Tomioka²,

Saito³

et al. 2015

20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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Combination of a air-breathing engines and rocket engines (termed as Rocket BasedCombined Cycle engine) gives an opportunity to reduce onboard oxygen consumption and to increase system weight margins for various application from cruiser to launch vehicles. For launch vehicle applications, combination of a ramjet/scramjet (supersonic combustion ramjet) flow-pass with embedded rocket engines was proposed (termed as Rocket-Ramjet Combined Cycle engine, T. Kanda, et. al., JPP, 19(2003), 859), and related R&D activities are undergoing at Japan Aerospace Exploration Agency (JAXA), Kakuda Space Center targeting hydrogen as the fuel due to its high Isp and cooling performances. Use of hydrogen fuel, on the other hand, can be costly due to the fuel cost and difficult-to-handle nature of liquefied hydrogen. Thus, hydrocarbon fuel such as ethanol was under consideration for the application to the future reusable launch vehicles termed as the 'reference system,' targeting manned operation to LEO. This presentation is to show the status of system analysis, flight demonstration plan, and related research efforts. Nomenclature AOA = angle of attack D = vehicle drag Fth = thrust Isp, Isp e = specific impulse, effective specific impulse O/F = rocket chamber mixture mass ratio p, P = static pressure, total pressure q = dynamic pressure W = weight X = streamwise location  = equivalence ratio Subscripts: a = airflow f = fuel p, p1 = propellant, propellant on booster stage r = rocket to = at take off 0 = at freestream or stagnant conditions

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Evaluation of Metallic-tube-cooled C/C Composite Structure by Rocket Combustor

Cited by 2 publications

References 3 publications

Application of Carbon Fiber‐Reinforced Ceramic Composites in Active Thermal Protection of Advanced Propulsion Systems: A Review

Application of Carbon Fiber‐Reinforced Ceramic Composites in Active Thermal Protection of Advanced Propulsion Systems: A Review

R&D on Hydrocarbon-fueled RBCC Engines for a TSTO Launch Vehicle

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