Technology developments for thrust chambers of future launch vehicle liquid rocket engines

Immich, H.; Alting, J.; Kretschmer, J.; Preclik, D.

doi:10.1016/s0094-5765(03)80021-8

Cited by 16 publications

(2 citation statements)

References 6 publications

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“…Only a few studies can be found in the literature about heat transfer enhancement in rocket thrust chambers. In particular, experimental tests have been conducted on ribbed plates [8] and cylinders [9] as preparatory programs to identify suitable test equipment and investigate rib geometry effects in engine-like conditions. A calorimetric sub-scale hydrogen=oxygen chamber has been investigated experimentally [10] and numerically [11] with and without ribs.…”

Section: Introductionmentioning

confidence: 99%

Numerical Evaluation of Heat Transfer Enhancement in Rocket Thrust Chambers by Wall Ribs

Betti

Nasuti

Martelli

2014

Numerical Heat Transfer, Part A: Applications

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Heat transfer enhancement due to longitudinal wall ribs inserted in a rocket engine thrust chamber is analyzed by means of a Reynolds-Averaged Navier-Stokes equations solver. A ribbed wall experiment is numerically reproduced to assess the capability of the simplified approach to properly capture the heat transfer enhancement. Then, a parametric analysis on the role of the longitudinal rib height on heat transfer enhancement is made on a sample thrust chamber. Results show the expected heat increase related to the surface increase, and highlight the reduction of efficiency for increasing rib height due to the thermal stratification between ribs.

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Section: Introductionmentioning

confidence: 99%

Numerical Evaluation of Heat Transfer Enhancement in Rocket Thrust Chambers by Wall Ribs

Betti

Nasuti

Martelli

2014

Numerical Heat Transfer, Part A: Applications

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“…Schmidt et al (1998) has shown that the most efficient and straightforward design measure for increasing heat transfer of rocket chamber is decreasing of the hot gas wall surface temperature in the thrust chamber. Three concepts for enhancing heat transfer to the coolant have been selected and investigated experimentally by comprehensive subscale chamber hot-fire tests (Immich et al, 2003): increasing the length of chamber cylinder, increasing the number of hot gas wall side ribs and artificially increasing the surface roughness. Heat transfer simulation and analysis of single geometrical parameter of liquid rocket cooling channel have been fulfilled, and the enhanced heat transfer by ribs has been reported in Immich et al (1999Immich et al ( , 2000.…”

Section: Introductionmentioning

confidence: 99%

Numerical simulation and optimization on heat transfer and fluid flow in cooling channel of liquid rocket engine thrust chamber

Wang

Wu²,

Zeng³

et al. 2006

Engineering Computations

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Purpose -To find the optimal number of channels of rocket engine thrust chamber, it was found that the optimal channel number is 335, at which the cooling effect of the thrust chamber cooling channel reaches the best, which can be helpful to design rocket engine thrust chamber. Design/methodology/approach -The commercial computational fluid dynamics (CFD) software FLUENT with standard k-1 turbulent model was used. The CFD method was validated via comparing with the available experimental data. Findings -It was found that both the highest temperature and the maximal heat flux through the wall on the hot-gas side occurs about the throat region at the symmetrical center of the cooling channel. Owing to the strong curvature of the cooling channel geometry, the secondary flow reached its strongest level around the throat region. The typical values of pressure drop and temperature difference between the inlet and exit of cooling channel were 2.7 MPa and 67.38 K (standard case), respectively. Besides an optimal number of channels exist, and it is approximately 335, which can make the effect of heat transfer of cooling channels best with acceptable pressure drop. As a whole, the present study gives some useful information to the thermal design of liquid rocket engine thrust chamber. Research limitations/implications -More detailed computation and optimization should be performed for the fluid flow and heat transfer of cooling channel. Practical implications -A very useful optimization on heat transfer and fluid flow in cooling channel of liquid rocket engine thrust chamber. Originality/value -This paper provides the performance of optimization on heat transfer and fluid flow in cooling channel of liquid rocket engine thrust chamber, which can make the effect of heat transfer of cooling channels best with acceptable pressure drop. As a whole, the present study gives some useful information to the thermal design of liquid rocket engine thrust chamber.

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Design and Testing of a C/C‐Sic Nozzle Extension Manufactured Via Filament Winding Technique and Liquid Silicon Infiltration

Breede

Jemmali

Voggenreiter

et al. 2014

Ceramic Transactions Series

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Technology developments for thrust chambers of future launch vehicle liquid rocket engines

Cited by 16 publications

References 6 publications

Numerical Evaluation of Heat Transfer Enhancement in Rocket Thrust Chambers by Wall Ribs

Numerical Evaluation of Heat Transfer Enhancement in Rocket Thrust Chambers by Wall Ribs

Numerical simulation and optimization on heat transfer and fluid flow in cooling channel of liquid rocket engine thrust chamber

Design and Testing of a C/C‐Sic Nozzle Extension Manufactured Via Filament Winding Technique and Liquid Silicon Infiltration

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