High Frequency Quantitative Photoelasticity Applied to Jet Engine Components

2006 ◽  
Vol 46 (6) ◽  
pp. 661-668 ◽  
Author(s):  
E. Patterson ◽  
P. Brailly ◽  
M. Taroni
Alloy Digest ◽  
1952 ◽  
Vol 1 (2) ◽  

Abstract Flylite ZRE-1 is a creep resistant magnesium-base alloy primarily designed for jet engine components and other high temperature applications. This datasheet provides information on composition, physical properties, hardness, elasticity, tensile properties, and compressive strength as well as creep. It also includes information on high temperature performance as well as casting, heat treating, machining, and joining. Filing Code: Mg-2. Producer or source: Howard Foundry Company.


Author(s):  
Jian Feng

AbstractThe purpose of the present study is to determine the cause of failures of semisolid rheocast cylinder head covers of hypereutectic modified LM30 alloys. The covers, manufactured by rheocasting, a process that consists of the incorporation and homogeneous distribution of the reinforcements in semisolid metal (SSM) before die casting, were shot-peened after heat treatment to increase the fatigue resistance. However, these engine components failed during operation after a short service time. The major flaws were located by radiography. The microstructure was controlled by metallography. Significant interactions between shot peening and surface/subsurface contaminants were identified by surface morphology and fractography. The fatigue properties of hypereutectic alloys were investigated by a high-frequency vibrophore. It was identified that the failure was related to the cleanliness of SSM as well as the rheocasting process. Recommendations were given to prevent the recurrence of similar failures.


Author(s):  
A. Fischersworring ◽  
W. Koschel

The assessment of fatigue-creep life of hot engine components either using conventional safe life design approach or damage tolerant design concepts require the computation and evaluation of the stress-strain-temperature-time cycles corresponding to the operational sequences. For typical jet engine operations the temperature and elastic stress-strain states for an uncooled turbine blade were calculated using finite elements. A primary concern was the aspect of multiaxiality and associated non-proportionality. The results are discussed in regard to multiaxial equivalent damage concepts.


Alloy Digest ◽  
1962 ◽  
Vol 11 (1) ◽  

Abstract Ti-8A1-1Mo-1V is a titanium alloy having excellent creep resistance and stress-rupture life. It is recommended for jet engine components operating up to 900 F. This datasheet provides information on composition, physical properties, elasticity, tensile properties, and shear strength as well as fracture toughness and creep. It also includes information on high temperature performance as well as forming, heat treating, machining, and joining. Filing Code: Ti-32. Producer or source: Titanium Metals Corporation of America.


2021 ◽  
Author(s):  
Paul G. A. Cizmas

Get up to speed with this robust introduction to the aerothermodynamics principles underpinning jet propulsion, and learn how to apply these principles to jet engine components. Suitable for undergraduate students in aerospace and mechanical engineering, and for professional engineers working in jet propulsion, this textbook includes consistent emphasis on fundamental phenomena and key governing equations, providing students with a solid theoretical grounding on which to build practical understanding; clear derivations from first principles, enabling students to follow the reasoning behind key assumptions and decisions, and successfully apply these approaches to new problems; practical examples grounded in real-world jet propulsion scenarios illustrate new concepts throughout the book, giving students an early introduction to jet and rocket engine considerations; and online materials for course instructors, including solutions, figures, and software resources, to enhance student teaching.


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