Life prediction methodology for aircraft gas turbine engine disks

Mahorter, Robert G.; London, Gérard M.; Fowler, S.H.; Salvino, J T

doi:10.2514/6.1985-1141

Cited by 6 publications

(7 citation statements)

References 1 publication

Supporting

Mentioning

Contrasting

Order By: Relevance

“…By establishing a probabilistic model for crack growth in aero-disks, it is possible to effectively express the uncertain information involved in the crack growth process and accurately estimate the real performance of aero-disks. 6 In this paper, Paris-Erdogan model is chosen to analyze fatigue crack growth of aero-disks, which can be expressed as follows 53…”

Section: Fatigue Reliability Model Based On Crack Growthmentioning

confidence: 99%

“…The reliability design concept was first applied on engine disk in the United States, and they established a reliability design system for disk structure. 6 Liu and Mahadevan proposed a probability model for random variables that takes into account the influence of stress intensity factor threshold. 7 In this model, material properties and stress intensity factor threshold are treated as random variables.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Fatigue reliability and sensitivity analysis of aero‐disk considering correlation

Di,

Li,

Nan

et al. 2024

Quality & Reliability Eng

View full text Add to dashboard Cite

Aero‐disk is a key component of aero‐engine. Due to its complex working conditions, aero‐disk is prone to structural failures. Therefore, it is essential to analyze the reliability and importance input variables of aero‐disk. In this paper, a framework of aero‐disk reliability analysis and global sensitivity analysis (GSA) was established. First, the hazardous regions of aero‐disk were determined by finite element analysis, and the limit state function of aero‐disk was defined by the life interference model. Then D‐Vine model was utilized to establish the correlation model for aero‐disk hazardous regions to evaluate the reliability of aero‐disk. In addition, two GSA methods based on Copula and space partition were proposed to identify important input random variables considering underlying correlation, and the accuracy of the proposed method was verified by two examples. Finally, the proposed method was applied to the GSA of aero‐disk. The results show that the established framework fills in the gap of uncertainty analysis of aero‐disk, which can be extended to other engineering fields. The proposed GSA methods have both high efficiency and accuracy and can realize multi‐dimensional GSA when the correlation of input variables is considered.

show abstract

Section: Fatigue Reliability Model Based On Crack Growthmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Fatigue reliability and sensitivity analysis of aero‐disk considering correlation

Di,

Li,

Nan

et al. 2024

Quality & Reliability Eng

View full text Add to dashboard Cite

show abstract

“…The second example is a quarter model of a spinning turbine disk. Such a model was considered by Mahorter et al [39], who examined the fatigue life for various crack locations in two sets of turbine disks. A similar turbine disk model ( Figure 21) was created and analysed here.…”

Section: Rotating Turbine Disk With Planar Crackmentioning

confidence: 99%

“…Using the Forman}Newman}deKoning [40,41] fatigue crack growth model and the material parameters from Table I, the predicted fatigue life for the disk starting from an initial corner crack on the bolthole-disk surface with radius 0)76 mm is about Table I Figure 25). Mahorter et al [39] report that the low cycle fatigue (LCF) life of the disk ends when the crack in the bolthole reaches 1/32 in (0)79 mm); this corresponds to the B.1 life which is expressed as a 1/1000 probability of failure. The analyses presented here provide an estimate of remaining life of the disk once the LCF life is reached.…”

Section: Rotating Turbine Disk With Planar Crackmentioning

confidence: 99%

Automated 3-D crack growth simulation

Carter

Wawrzynek

Ingraffea

2000

Int. J. Numer. Meth. Engng.

149

View full text Add to dashboard Cite

Automated simulation of arbitrary, non-planar, 3-D crack growth in real-life engineered structures requires two key components: crack representation and crack growth mechanics. A model environment for representing the evolving 3-D crack geometry and for testing various crack growth mechanics is presented. Reference is made to a speci"c implementation of the model, called FRANC3D. Computational geometry and topology are used to represent the evolution of crack growth in a structure. Current 3-D crack growth mechanics are insu$cient; however, the model allows for the implementation of new mechanics. A speci"c numerical analysis program is not an intrinsic part of the model, i.e. "nite and boundary elements are both supported. For demonstration purposes, a 3-D hypersingular boundary element code is used for two example simulations. The simulations support the conclusion that automatic propagation of a 3-D crack in a real-life structure is feasible. Automated simulation lessens the tedious and time-consuming operations that are usually associated with crack growth analyses. Speci"cally, modi"cations to the geometry of the structure due to crack growth, remeshing of the modi"ed portion of the structure after crack growth and reapplication of boundary conditions proceeds without user intervention.

show abstract

“…Melis and Ogonek (1995) implemented this life-prediction methodology through a computer code called Probable Cause. Melis, Zaretsky, and August (1999), using the method of Zaretsky and the computer code Probable Cause, analyzed the lives of two different groups of aircraft gas turbine engine compressor disks for which there existed limited fatigue data (Mahorter et al, 1985). These disks were manufactured from a titanium (Ti-6Al-4V) alloy.…”

Section: Figurementioning

confidence: 99%

Weibull‐Based Design Methodology for Rotating Structures in Aircraft Engines

Zaretsky

Hendricks

Soditus

2003

International Journal of Rotating Machinery

View full text Add to dashboard Cite

The NASA Energy-Efficient Engine (E 3 -Engine) is used as the basis of a Weibull-based life and reliability analysis. Each component's life, and thus the engine's life, is defined by high-cycle fatigue or low-cycle fatigue. Knowing the cumulative life distribution of each of the components making up the engine as represented by a Weibull slope is a prerequisite to predicting the life and reliability of the entire engine. As the engine's Weibull slope increases, the predicted life decreases. The predicted engine lives L 5 (95% probability of survival) of approximately 17,000 and 32,000 hr do correlate with current engine-maintenance practices without and with refurbishment, respectively. The individual high-pressure turbine (HPT) blade lives necessary to obtain a blade system life L 0.1 (99.9% probability of survival) of 9000 hr for Weibull slopes of 3, 6, and 9 are 47,391; 20,652; and 15,658 hr, respectively. For a design life of the HPT disks having probable points of failure equal to or greater than 36,000 hr at a probability of survival of 99.9%, the predicted disk system life L 0.1 can vary from 9408 to 24,911 hr.Keywords Design, Engine, Failure, Life, Turbine, WeibullThe classic approach to aircraft engine component design has been deterministic. The deterministic method assumes that full and certain knowledge exists for the service conditions and the material strength. Specific equations with specific material and fluid characteristics then define an engine component's operating conditions. They are coupled with experience-based safety factors to predict the component's performance, life, and

show abstract

Life prediction methodology for aircraft gas turbine engine disks

Cited by 6 publications

References 1 publication

Fatigue reliability and sensitivity analysis of aero‐disk considering correlation

Fatigue reliability and sensitivity analysis of aero‐disk considering correlation

Automated 3-D crack growth simulation

Weibull‐Based Design Methodology for Rotating Structures in Aircraft Engines

Contact Info

Product

Resources

About