3 edition of Probabilistic analysis of aircraft gas turbine disk life and reliability found in the catalog.
Probabilistic analysis of aircraft gas turbine disk life and reliability
by National Aeronautics and Space Administration, Glenn Research Center, National Technical Information Service, distributor in [Cleveland, Ohio], Springfield, VA
Written in English
|Statement||Matthew E. Melis, Erwin V. Zaretsky, Richard August.|
|Series||[NASA technical memorandum] -- NASA/TM-1999-107436., NASA technical memorandum -- 107436.|
|Contributions||Zaretsky, Erwin V., August, Richard., NASA Glenn Research Center.|
|The Physical Object|
Orthopaedic implants, as well as other physical systems, contain inherent variability in geometry, material properties, component alignment, and loading conditions. While complex, deterministic fin. “Probabilistic fretting fatigue assessment of aircraft engine disks,” Journal of Engineering for Gas Turbines and Power, ASME, (7), pp. Enright, M.P., et al. (). “Probabilistic treatment of crack formation and growth for gas turbine engine materials,” Journal of Engineering for Gas Turbines and Power, ASME, (8.
In the present work, a probabilistic framework for fatigue life prediction and reliability assessment of an engine high pressure turbine disc is proposed to incorporate the effects of load variations and mean stress, which provides a reference for engine structural design under a given target failure by: AbstractFuzzy and probability-box (p-box) variables exit widely in aerospace engineering. To evaluate the reliability of turbine discs under the mixture of these two types of variables and guarantee safety, the critical point lies in how to deal with the fuzzy variables. In this paper, a novel method based on equivalent transformation of entropy and saddlepoint approximation (SPA) is Cited by: 1.
WEIBULL PROBABILITY ANALYSIS A typical scenario that can be adopted to design an aircraft engine for life and reliability is to assume a typical ﬂight (pro-ﬁle) cycle and specify a life in ﬂight hours and a reliability for FIGURE 2 Cutaway of E3-engine ﬂight propulsion system (FPS) illustrating its features. (From Davis and Stearns, ). denotes the allowed LCF life of the gas turbine disc. The reliability probability value of the LCF life of gas turbine disc should be greater than or equal to % and the corresponding reliability index is which is obtained by: 1.
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PROBABILISTIC ANALYSIS OF AIRCRAFT GAS TURBINE DISK LIFE AND RELIABILITY Matthew E. Melis and Erwin V. Zaretsky National Aeronautics and Space Administration Glenn Research Center Cleveland, Ohio and Richard August NYMA, Inc.
Brook Park, Ohio ABSTRACT Two series of low-cycle-fatigue (LCF) test data for two different groups of File Size: 1MB. Probabilistic fatigue-creep life reliability assessment of aircraft turbine disk 7 December | Journal of Mechanical Science and Technology, Vol.
32, No. 11 Probabilistic failure risk assessment for aeroengine disks considering a transient processCited by: Probabilistic analysis of aircraft gas turbine disk life and reliability (OCoLC) Material Type: Government publication, National government publication: Document Type: Book: All Authors / Contributors: Matthew E Melis; Erwin V Zaretsky; Richard August; NASA Glenn Research Center.
Damage fraction summation is used to calculate the low cycle fatigue creep life and estimate the reliability assessment of turbine disk of civil aircraft . A control theoretic simulation.
A NASA Glenn Research Center developed probabilistic computer code Probable Cause was used to predict disk life and reliability. A material-life factor A was determined for titanium (Ti-6Al-4V) alloy based upon fatigue disk data and successfully applied to predict the life of the disks as a.
Two series of low cycle fatigue (LCF) test data for two groups of different aircraft gas turbine engine compressor disk geometries were reanalyzed and compared using Weibull statistics.
Both groups of disks were manufactured from titanium (Ti-6Al-4V) alloy. A NASA Glenn Research Center developed probabilistic computer code Probable Cause was used to predict disk life and reliability. The low cycle fatigue of turbine disk coming from the creep and their interaction has a direct influence on life and reliability of an aero engine.
So, in this paper, the finite element analysis fatigue creep on Nickel base super alloy GH turbine disk at °C is computed based on the material properties, load and performance parameter of the low cycle fatigue as a random by: 2.
Life prediction methodology for aircraft gas turbine engine disks. Probabilistic Analysis of Aircraft Gas Turbine Disk Life and Reliability. Matthew E. Melis, Probabilistic analysis of aircraft gas turbine disk life and reliability.
Matthew Melis. A probabilistic Physics of Failure-based framework for fatigue life prediction of aircraft gas turbine discs operating under uncertainty is developed.
On The Application of Probabilistic Methods for Gas Turbine Engines June 11 - 13, APPROACH--For Turbine Disks c_ Test to Failure in Spin Rig 10 Disks Retired for Time Develop Statistical Database for Disk Material For Life Prediction Purposes Apply Statistical Database to Disk Life PredictionAuthor: Jonathan S.
Litt, Sherry Soditus, Robert C. Hendricks, Erwin V. Zaretsky. A probabilistic Physics of Failure-based framework for fatigue life prediction of aircraft gas turbine discs operating under uncertainty is developed.
The framework incorporates the overall uncertainties appearing in a structural integrity assessment. A comprehensive uncertainty quantification (UQ) procedure is presented to quantify multiple types of uncertainty using multiplicative and additive UQ Cited by: Abstract. The second HP turbine rotor blade and disk are the key components of a type of aeroengine, for comparing the value of life consumption of the type of aeroengine in endurance test case with field service case, used finite element method to analyze the simulative steady temperature field and stress field of the second HP turbine rotor blade and : Yongqi Wang, Haibing Zhang, Shenhui Zhang, Tao Qin, Zhide Yu.
Various safety analysis methods have been proposed involving key structural components like engine cylinder heads, aeroengine disks, and aircraft spars.Variable amplitude loads, were considered to simulate the actual complex working conditions of aircrafts during the service period.
All these methods provide effective tool for the safety design of aircraft, and are thus : Shuiting Ding, Ziyao Wang, Tian Qiu, Gong Zhang, Guo Li, Yu Zhou.
Probabilistic analysis of aircraft gas turbine disk life and reliability (OCoLC) Material Type: Document, Government publication, National government publication, Internet resource: Document Type: Internet Resource, Computer File: All Authors / Contributors: Matthew E Melis; Erwin V Zaretsky; Richard August; NASA Glenn Research Center.
Application of Probabilistic Sensitivities to Probabilistic Fatigue Analysis of Gas Turbine Engine Disks R. Wesley Osborn*, Harry R. Millwater† University of Texas at San Antonio, San Antonio, Texas A methodology is presented and applied that determines the sensitivities of the probability-of-fracture of a gas turbine disk fatigue Cited by: 2.
Koul, Ashok K., Bhanot, Saurabh, Tiku, Ajay, and Junkin, Brent. "Improving Component Life Prediction Accuracy and Reliability Through Physics Based Prognosis: A Probabilistic Turbine Blade Case Study." Proceedings of the ASME Turbo Expo Power for Land, Sea, and by: 4.
Abstract: Risk and reliability assessment of aircraft gas turbine engines for the evaluation of component failure has received increasing interest in the last few years, fueled by the greater appreciation of stochastic models and the concern for airworthiness issues.
This report reviews the current status of probabilistic methods available for the risk and reliability assessment of gas. Over the past two decades there has been considerable effort by NASA Glenn and others to develop probabilistic codes to predict with reasonable engineering certainty the life and reliability of critical components in rotating machinery and, more specifically, in the rotating sections of airbreathing and rocket engines.
These codes have, to a very limited extent, been verified with relatively Author: Jonathan S. Litt, Sherry Soditus, Robert C. Hendricks, Erwin V. Zaretsky. A methodology is developed and applied that determines the sensitivities of the probability-of-fracture of a gas turbine disk fatigue analysis with respect to the parameters of the probability distributions describing the random variables.
The disk material is subject to initial anomalies, in either low- or high-frequency quantities, such that commonly used materials (titanium, nickel, powder Cited by: the current safe-life approach for low-cycle fatigue design of titanium disks/rotors in aircraft gas turbine engines.
DARWIN is a computer program that integrates finite element stress analysis, fracture mechanics analysis, nondestructive inspection simulation, and probabilistic analysis to assess the risk of rotor failure. It computes the. Fretting fatigue is a random process that continues to be a major source of damage associated with the failure of aircraft gas turbine engine components.
Fretting fatigue is dominated by the fatigue crack growth phase and is strongly dependent on Cited by: Probabilistic analysis of aircraft gas turbine disk life and reliability, (). Probabilistic risk analysis of a cemented hip implant.The Implementation of Probabilistic Methods for Uncertainty Analysis in Computational Fluid Dynamics Simulations of Fluid Flow and Heat Transfer in a Gas Turbine Engine Executive Summary DSTO has developed a risk and reliability management capability for mechanical components in .