Non-intrusive Diagnostic of Middle Bearing of Aircraft Engine

2015 ◽  
pp. 203-213
Author(s):  
Romuald Rzadkowski ◽  
Edward Rokicki ◽  
Ryszard Szczepanik ◽  
Józef Żurek
Keyword(s):  
Aircraft Engine

High-Temperature Instability of A Cr2Nb-Nb(Cr) Microlaminate Composite

1996 ◽  
Vol 54 ◽  
pp. 374-375
Author(s):  
M. Larsen ◽  
R.G. Rowe ◽  
D.W. Skelly
Keyword(s):  
Heat Treatment ◽  
Solid Solution ◽  
High Temperature ◽  
Elevated Temperatures ◽  
Aircraft Engine ◽  
Lattice Parameter ◽  
Microstructural Stability ◽  
Elevated Temperature Strength ◽  
Cross Sectional ◽  
Bcc Structure

Microlaminate composites consisting of alternating layers of a high temperature intermetallic compound for elevated temperature strength and a ductile refractory metal for toughening may have uses in aircraft engine turbines. Microstructural stability at elevated temperatures is a crucial requirement for these composites. A microlaminate composite consisting of alternating layers of Cr2Nb and Nb(Cr) was produced by vapor phase deposition. The stability of the layers at elevated temperatures was investigated by cross-sectional TEM.The as-deposited composite consists of layers of a Nb(Cr) solid solution with a composition in atomic percent of 91% Nb and 9% Cr. It has a bcc structure with highly elongated grains. Alternating with this Nb(Cr) layer is the Cr2Nb layer. However, this layer has deposited as a fine grain Cr(Nb) solid solution with a metastable bcc structure and a lattice parameter about half way between that of pure Nb and pure Cr. The atomic composition of this layer is 60% Cr and 40% Nb. The interface between the layers in the as-deposited condition appears very flat (figure 1). After a two hour, 1200 °C heat treatment, the metastable Cr(Nb) layer transforms to the Cr2Nb phase with the C15 cubic structure. Grain coarsening occurs in the Nb(Cr) layer and the interface between the layers roughen. The roughening of the interface is a prelude to an instability of the interface at higher heat treatment temperatures with perturbations of the Cr2Nb grains penetrating into the Nb(Cr) layer.

Report and discussion on “A philosophy of aircraft engine manufacture”

1965 ◽  
Vol 44 (7) ◽  
pp. 344
Author(s):  
L.R. Beesly ◽  
Morley ◽  
W.S. Hollis ◽  
Higson Smith ◽  
G.A.J. Witton ◽  
...  
Keyword(s):  
Aircraft Engine

Electro-impulse de-icing of aircraft engine inlets

1986 ◽  
Author(s):  
D. NELEPOVITZ ◽  
H. ROSENTHAL
Keyword(s):  
Aircraft Engine

CRUCIBLE 347

Alloy Digest ◽  
1983 ◽  
Vol 32 (12) ◽  
Keyword(s):  
Fracture Toughness ◽  
Corrosion Resistance ◽  
High Temperature ◽  
Aircraft Engine ◽  
Heat Treating ◽  
Nickel Steel ◽  
Annealed Condition ◽  
Engine Exhaust ◽  
Cold Worked ◽  
Specialty Metals

Abstract CRUCIBLE F347 is a non-hardenable austenitic chromium-nickel steel that is particularly adaptable for use at temperatures between 800 and 1650 F. It is non-magnetic in the annealed condition but is slightly magnetic in the cold-worked condition. Among its many applications are aircraft-engine exhaust manifolds, boiler shells and high-temperature handling equipment. This datasheet provides information on composition, physical properties, hardness, elasticity, and tensile properties as well as fracture toughness. It also includes information on corrosion resistance as well as forming, heat treating, machining, and joining. Filing Code: SS-436. Producer or source: Crucible Specialty Metals Division, Colt Industries.

CRUCIBLE 321

Alloy Digest ◽  
1983 ◽  
Vol 32 (5) ◽  
Keyword(s):  
Fracture Toughness ◽  
Aircraft Engine ◽  
Heat Treating ◽  
Nickel Steel ◽  
Annealed Condition ◽  
Engine Exhaust ◽  
Expansion Joints ◽  
Temperature Performance ◽  
Cold Worked ◽  
Specialty Metals

Abstract CRUCIBLE 321 is a non-hardenable austenitic chromium-nickel steel which is particularly adaptable for parts fabricated by welding without postweld annealing for use at temperatures between 800 and 1500 F. This grade is non-magnetic in the annealed condition but is slightly magnetic when cold worked. Among its many applications are aircraft-engine exhaust manifolds, furnace parts and expansion joints. This datasheet provides information on composition, physical properties, hardness, elasticity, and tensile properties as well as fracture toughness and creep. It also includes information on high temperature performance and corrosion resistance as well as forming, heat treating, machining, and joining. Filing Code: SS-426. Producer or source: Crucible Specialty Metals Division, Colt Industries.

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