New Concepts in Structural Analysis and Design of Double Walled LPRE Thrust Chambers

Asraff, A. K.; Sunil, S.; Muthukumar, R.; Ramanathan, T. J.

doi:10.2514/6.2006-4368

Cited by 2 publications

(3 citation statements)

References 2 publications

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“…Thermal and pressure loads were applied in 7 different load steps simulating the complete sequence of hot testing of the chamber viz. (i) pre-chilling (ii) start up transient (iii) steady state combustion (iv) creep for a duration of 6500 seconds (v) shut down transient (vi) post chilling and (vii) unloading to ambient [3]. The duration of operation of the thrust chamber at peak load is 650 s and a factor of safety of 10 has been used to arrive at the creep analysis duration of 6500 s. Cross-section considered is at a distance of 350 mm from injector end (near throat). "…”

Section: Two Dimensional Cyclic Stress Analysis Of Thrust Chambermentioning

confidence: 99%

“…The value of Δε is obtained as explained in " Fig.18" for two dimensional plane strain cross section using the Creep + MISO model. The cyclic damage factor LCF f is calculated as [2,3]…”

Section: Fatigue Life Predictionmentioning

confidence: 99%

“…Cyclic stress analysis of two dimensional finite element model of thrust chamber (either plane strain, plane stress or axisymmetric) is described in [2][3][4][5]. No effort was made so far to model the three dimensional nature of the chamber.…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Fatigue Life Prediction of a Rocket Combustion Chamber

Babu¹,

Asraff²,

Philip³

2014

IOSRJMCE

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Cryogenic engines are commonly used in rockets for launching geosynchronous class satellites. The thrust chamber of cryogenic engines is generally of double walled construction. A high conductivity copper alloy is usually selected for the inner wall in regions of high heat flux and for other regions stainless steel is chosen. The failure of a thrust chamber is due to low cycle fatigue, creep of the inner wall, and thermal ratcheting. Present work deals with the study of different plasticity models for the cyclic stress analysis of a double walled cryogenic rocket engine thrust chamber. The work is done using ANSYS (Version 15) finite element code. Different plasticity models used for a simple cubic block showed that a combination of Chaboche's non linear kinematic hardening model in association with multilinear isotropic hardening and creep models is the best suited for cyclic stress analysis of the chamber. Cu-Cr-Zr-Ti alloy is investigated here as it is used in the inner wall of the thrust chamber. Material properties are taken from literature. A comparison of two dimensional (plane strain) and three dimensional cross section of thrust chamber is done. Cyclic life of the chamber is calculated from the cyclic stress-strain graph obtained from above analyses.

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Section: Two Dimensional Cyclic Stress Analysis Of Thrust Chambermentioning

confidence: 99%

“…The value of Δε is obtained as explained in " Fig.18" for two dimensional plane strain cross section using the Creep + MISO model. The cyclic damage factor LCF f is calculated as [2,3]…”

Section: Fatigue Life Predictionmentioning

confidence: 99%