Stress analysis &amp; life prediction of a cryogenic rocket engine thrust chamber considering low cycle fatigue, creep and thermal ratchetting

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

doi:10.1007/s12666-010-0089-7

Cited by 10 publications

(5 citation statements)

References 4 publications

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“…The average temperatures of the inner wall ligament and closeout wall by Ti and T0, respectively. The inelastic strain range of the Porowski mod modified model are given by Equations ( 1) and (2). Ti and T0 can be calculat tions (3) and (4).…”

Section: Inelastic Strainmentioning

confidence: 99%

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Life Analysis of Reusable Liquid Rocket Engine Thrust Chamber

Cheng

Zhang

2022

Aerospace

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The thrust chamber’s inner wall suffers high temperature and pressure differences from the coolant channel, which limits the life of the rocket engine. Life prediction of the thrust chamber really plays an important role in reusable launch vehicle propulsion systems. The Porowski beam model is widely used in the life prediction of reusable liquid rocket engine thrust chambers, which calculates the life caused by fatigue, creep, and thinning after each firing cycle. In order to analyze the life of the thrust chamber, a LOX/Kerosene rocket engine is investigated in this paper. The life analysis consists of pressure and temperature differences and structural parameters. Two kinds of inner wall materials were chosen for comparison in this research: OFHC copper and Narloy-Z alloy. The results are presented to offer a reference for the design and manufacture of reusable rocket engine thrust chambers in the future.

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Section: Inelastic Strainmentioning

confidence: 99%

“…A.K. Asraff [2,3] performed a stress analysis and cyclic and creep life prediction of a cryogenic rocket engine thrust chamber materials by ANSYS finite element analysis software package. The failure mode of stainless steel and copper alloys are creep and low cycle fatigue (LCF).…”

Section: Introductionmentioning

confidence: 99%

Life Analysis of Reusable Liquid Rocket Engine Thrust Chamber

Cheng

Zhang

2022

Aerospace

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“…The number of cells (meshes) is required by the convergence analyses of the responses [15,32,33]. The FE basic equations of the bladed disk comprising a shape function of the tetrahedron in Equation (14) [34], geometric equation in Equation (15) [35], physical equation in Equation (16) [36], and Norton implicit creep equation in Equation (17) [37] are analyzed with regard to the means of the parameters in Table 1. From this analysis, the distributions of the creep stress and creep strain of the bladed disk are drawn in Figure 5, Figure 6, Figure 7 and Figure 8.…”

Section: Fuzzy Probabilistic Fatigue/creep Optimization Of Turbinementioning

confidence: 99%

Probabilistic Fatigue/Creep Optimization of Turbine Bladed Disk with Fuzzy Multi-Extremum Response Surface Method

et al. 2019

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To effectively perform the probabilistic fatigue/creep coupling optimization of a turbine bladed disk, this paper develops the fuzzy multi-extremum response surface method (FMERSM) for the comprehensive probabilistic optimization of multi-failure/multi-component structures, which absorbs the ideas of the extremum response surface method, hierarchical strategy, and fuzzy theory. We studied the approaches of FMERSM modeling and fatigue/creep damage evaluation of turbine bladed disks, and gave the procedure for the fuzzy probabilistic fatigue/creep optimization of a multi-component structure with FMERSM. The probabilistic fatigue/creep coupling optimization of turbine bladed disks was implemented by regarding the rotor speed, temperature, and density as optimization parameters; the creep stress, creep strain, fatigue damage, and creep damage as optimization objectives; and the reliability and GH4133B fatigue/creep damages as constraint functions. The results show that gas temperature T and rotor speed ω are the key parameters that should be controlled in bladed disk optimization, and respectively reduce by 85 K and 113 rad/s after optimization, which is promising to extend bladed disk life and decrease failure damages. The simulation results show that this method has a higher modeling accuracy and computational efficiency than the Monte Carlo method (MCM). The efforts of this study provide a new useful method for overall probabilistic multi-failure optimization and enrich mechanical reliability theory.

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“…Liquid engines are critical components for space rocket, thus the service life must be fully considered to satisfy the requirement of reuse and safety. For example, potential failure mode in a high-temperature rocket engine thrust chamber can be quite complex as it combines multiple failure mechanisms, including low-cycle fatigue (LCF), creep and thermal ratcheting of inner walls (Asraff et al, 2002). Damage caused by LCF may be due to the cyclic thermal stress in the elasto-plastic region during engine start-up and shutdown (Asraff et al, 2010).…”

Section: Introductionmentioning

confidence: 99%

“…For example, potential failure mode in a high-temperature rocket engine thrust chamber can be quite complex as it combines multiple failure mechanisms, including low-cycle fatigue (LCF), creep and thermal ratcheting of inner walls (Asraff et al, 2002). Damage caused by LCF may be due to the cyclic thermal stress in the elasto-plastic region during engine start-up and shutdown (Asraff et al, 2010). The inner wall of thrust chambers has a large diameter and thin thickness, it works at an extremely high temperature and pressure and is also impacted by high-speed hot gas (Rajasegar et al, 2021).…”

Section: Introductionmentioning

confidence: 99%

An investigation on the cyclic deformation and service life of a reusable liquid rocket engine thrust chamber wall

Gao¹,

Zhang²,

Huo³

2023

MMMS

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PurposeRegeneratively cooled thrust chamber is a key component of reusable liquid rocket engines. Subjected to cyclic thermal-mechanical loadings, its failure can seriously affect the service life of engines. QCr0.8 copper alloy is widely used in thrust chamber walls due to its excellent thermal conductivity, and its mechanical and fatigue properties are essential for the evaluation of thrust chamber life. This paper contributes to the understanding of the damage mechanism and material selection of regeneratively cooled thrust chambers for reusable liquid rocket engines.Design/methodology/approachIn this paper, tensile and low-cycle fatigue (LCF) tests were conducted for QCr0.8 alloy, and a Chaboche combined hardening model was established to describe the elastic-plastic behavior of QCr0.8 at different temperatures and strain levels. In addition, an LCF life prediction model was established based on the Manson–Coffin formula. The reliability and accuracy of models were then verified by simulations in ABAQUS. Finally, the service life was evaluated for a regenerative cooling thrust chamber, under the condition of cyclic startup and shutdown.FindingsIn this paper, a Chaboche combined hardening model was established to describe the elastoplastic behavior of QCr0.8 alloy at different temperatures and strain levels through LCF experiments. The parameters of the fitted Chaboche model were simulated in ABAQUS, and the simulation results were compared with the experimental results. The results show that the model has high reliability and accuracy in characterizing the viscoplastic behavior of QCr0.8 alloy.Originality/value(1)The parameters of a Chaboche combined hardening constitutive model and LCF life equation were optimized by tensile and strain-controlled fatigue tests of QCr0.8 copper alloy. (2) Based on the Manson–Coffin formula, the reliability and accuracy of constitutive model were then verified by simulations in ABAQUS. (3)Thermal-mechanical analysis was carried out for regeneratively cooled thrust chamber wall of a reusable liquid rocket engine, and the service life considering LCF, creep and ratcheting damage was analyzed.

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Stress analysis & life prediction of a cryogenic rocket engine thrust chamber considering low cycle fatigue, creep and thermal ratchetting

Cited by 10 publications

References 4 publications

Life Analysis of Reusable Liquid Rocket Engine Thrust Chamber

Life Analysis of Reusable Liquid Rocket Engine Thrust Chamber

Probabilistic Fatigue/Creep Optimization of Turbine Bladed Disk with Fuzzy Multi-Extremum Response Surface Method

An investigation on the cyclic deformation and service life of a reusable liquid rocket engine thrust chamber wall

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