Simplified design and life prediction of rocket thrust chambers

Porowski, J.S.; O’Donnell, W. J.; Badlani, M. L.; Kasraie, B.; Kasper, H. J.

doi:10.2514/3.25729

Cited by 17 publications

(16 citation statements)

References 3 publications

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“…Furthermore, in both models, the ligament compressive stresses in the tangential direction, highlighted in the hot phase, remain compressive up to the end of the creep period. In other words, temperature and stress values detected during the hot phase, are such that creep damage can be considered negligible, as demonstrated in [ 27 ], where stress-time curves are reported for temperature values higher than those encountered in the present test case. Therefore, no creep failure predictions were needed for the life assessment.…”

Section: Resultsmentioning

confidence: 53%

“…Therefore, no creep failure predictions were needed for the life assessment. Alternatively, creep failure can become dominant when higher thrust levels are required [ 27 ].…”

Section: Resultsmentioning

confidence: 99%

“…Hence, the temperature field influences the strain/stress response, and not vice versa. Several papers from literature demonstrated that such an approximation provided accurate results [ 26 , 27 , 28 , 29 ].…”

Section: Structural Modelmentioning

confidence: 99%

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Thermostructural Numerical Analysis of the Thrust Chamber of a Liquid Propellant Rocket Engine

et al. 2022

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The numerical simulation of rocket engine thrust chambers is very challenging as several damaging phenomena, such as plasticity, low-cycle-fatigue (LCF) and creep occur during its service life. The possibility of simulating the thermostructural behavior of the engine, by means of non-linear finite element analyses, allows the engineers to guarantee the structural safety of the structure. This document reports the numerical simulations developed with the aim of predicting the thermostructural behaviour and the service life of the thrust chamber of a liquid-propellant rocket engine. The work represents a step ahead of previous researches by the authors, with particular reference to the addition of the Smith-Watson-Topper (SWT) fatigue criterion, and to the implementation of a sub-modelling technique, for a more accurate assessment of the most critical section of the component. It was found that the equivalent plastic strains in the most critical nodes obtained through the sub-modelling technique were about 20% lower than those calculated without sub-modelling. Consistently with experimental tests from literature conducted on similar geometries, the most critical areas resulted to be on the internal surface of the chamber. The analyses demonstrated that the LCF damaging contribution was significant, with a life prediction for the thrust chamber of about 3400 cycles.

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Section: Resultsmentioning

confidence: 53%

“…Therefore, no creep failure predictions were needed for the life assessment. Alternatively, creep failure can become dominant when higher thrust levels are required [ 27 ].…”

Section: Resultsmentioning

confidence: 99%

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Thermostructural Numerical Analysis of the Thrust Chamber of a Liquid Propellant Rocket Engine

et al. 2022

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“…Cook et al [3] reported the occurrence of mid-channel wall thinning and deformation of the space shuttle main engine combustion chamber after hot firing tests and summarized the life prediction method based on fatigue-creep interaction. Porowski et al [4] developed a simplified life prediction method using a rectangular beam model for damage analysis of a cooling channel ligament. Dai and Ray [5] improved this method by applying the concepts of sandwich beam approximation and viscoplasticity to the model to improve the non-linear effects of creep and plasticity interactions.…”

Section: Introductionmentioning

confidence: 99%

“…Porowski et al . [ 4 ] developed a simplified life prediction method using a rectangular beam model for damage analysis of a cooling channel ligament. Dai and Ray [ 5 ] improved this method by applying the concepts of sandwich beam approximation and viscoplasticity to the model to improve the non-linear effects of creep and plasticity interactions.…”

Section: Introductionmentioning

confidence: 99%

Feasibility study on a neutron diffraction method for non-destructive evaluation of residual strain distribution of a combustion chamber

Moriya

Masuoka

Suzuki

2011

Proceedings of the Institution of Mechanical Engineers, Part G:

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A regeneratively cooled combustion chamber of a cryogenic liquid rocket engine is exposed to a large temperature difference between a combustion gas and a liquid hydrogen coolant. The large temperature difference induces large thermal stress in the chamber wall, and the strain is accumulated throughout the cyclic firing tests. Evaluation of the stress and the strain distribution in a chamber wall is essential for chamber life prediction because the chamber life is related to such stress and strain. A feasibility study on a neutron diffraction method for evaluation of residual strain distribution in a chamber wall was conducted. A method of positioning cooling channels inside a combustion chamber was established. The measurement time was adjusted to improve the fluctuation of the diffraction data. The measured data were compared with the numerical data by finite element analysis.

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Study of the Effects of Materials Selection for the Closeout Structure on the Service Life of a Liquid Rocket Engine Thrust Chamber

Ferraiuolo

Riccio

2019

J. of Materi Eng and Perform

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Simplified design and life prediction of rocket thrust chambers

Cited by 17 publications

References 3 publications

Thermostructural Numerical Analysis of the Thrust Chamber of a Liquid Propellant Rocket Engine

Thermostructural Numerical Analysis of the Thrust Chamber of a Liquid Propellant Rocket Engine

Feasibility study on a neutron diffraction method for non-destructive evaluation of residual strain distribution of a combustion chamber

Study of the Effects of Materials Selection for the Closeout Structure on the Service Life of a Liquid Rocket Engine Thrust Chamber

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