New PDF release: B0731 Life assessment of hot section gas turbine componets

By R. Townsend

ISBN-10: 1861251084

ISBN-13: 9781861251084

Those lawsuits of a convention held at Heriot Watt collage, Edinburgh, united kingdom conceal the real problems with either aero and commercial engines. The serious concerns linked to layout, creep and fatigue crack development, coating applied sciences, new fabrics, fix and upkeep of sizzling part elements have been lined

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Extra resources for B0731 Life assessment of hot section gas turbine componets

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Std. ' Publisher? 8. ]. Harris, 'Engine Component Retirement for Cause, Experimental Summary,' AFWALTR-87-4069. 9. H. ' Trans. , (1961), 28, 544-550. 10. G. Glinka, 'Calculation of Inelastic Notch Tip Stress-Strain Histories under Cyclic Loading,' Eng. Fracture Mechanics, (1985), 22(5), 839-854. 11. M. Hoffman and T. Seeger, 'Generalised Method for Estimating Multiaxial Elastic-Plastic Notch Stresses and Strains, Part 1: Theory, Part 2; Application and General Discussion,' ASME Journal of Engineering Materials Technology, (1985), 107, 250-260.

D. Brentnall, 'Operating Temperature Estimation and Life Assessment of Turbine Blade Airfoils', Proc. Con! Life Assessment & Repair Technology for Combustion Turbine Hot Section Components, EPRI/ASM, 1990. 9. M. McColvin, Technical Report 3296 for COST-SO/II Project UK 6, 1980, Henry Wiggin referred to in Summary of Physical and Mechanical Property Data of Ni-Base Superalloy In-738, COST Report 81-UW-COST-Bl by R Stickler, 1981. 10. V. S. ]. Carr and M. O'Brien, 1995, 'Degradation of MCrAlY Coating and Substrate Superalloy during Long-Term Thermal Exposure', Materials and Manufacturing Processes, 1995, 10, 955-969.

Since a larger volume of stressed material has a greater probability of containing a weak link, statistically it should have a shorter fatigue life. To enable read across from plane specimen data to notch data for specimens or components an equivalent size factor can be applied. For the present study the surface qualities were considered as fatigue critical and the different notch root areas were compared with the surface area of the plane test pieces. e. Pswrlife) curve in the loading direction (Fg> 1 shifts the curve upwards).

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B0731 Life assessment of hot section gas turbine componets by R. Townsend


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