De-alloying and fatigue of high temperature alloys used for gas turbine blades

1996 ◽  
Vol 37 (3) ◽  
pp. 209
Author(s):  
L.B. Getsov
Keyword(s):  
High Temperature ◽  
Gas Turbine ◽  
Turbine Blades ◽  
Gas Turbine Blades ◽  
High Temperature Alloys

De-alloying and fatigue of high temperature alloys used for gas turbine blades

1995 ◽  
Vol 13 (2) ◽  
pp. 81-86 ◽  
Author(s):  
L. B. Getsov ◽  
A. I. Rybnikov ◽  
P. G. Krukovski ◽  
E. C. Kartavova
Keyword(s):  
High Temperature ◽  
Gas Turbine ◽  
Turbine Blades ◽  
Gas Turbine Blades ◽  
High Temperature Alloys

UDIMET L-605

Alloy Digest ◽  
2004 ◽  
Vol 53 (12) ◽  
Keyword(s):  
Corrosion Resistance ◽  
High Temperature ◽  
Physical Properties ◽  
Tensile Properties ◽  
Gas Turbine ◽  
Oxidation Resistance ◽  
Turbine Blades ◽  
Heat Treating ◽  
Gas Turbine Blades ◽  
Temperature Performance

Abstract Udimet L-605 is a high-temperature aerospace alloy with excellent strength and oxidation resistance. It is used in applications such as gas turbine blades and combustion area parts. This datasheet provides information on composition, physical properties, and tensile properties as well as creep. It also includes information on high temperature performance and corrosion resistance as well as forming, heat treating, and joining. Filing Code: CO-109. Producer or source: Special Metals Corporation.

High Temperature Degradation of Coating and Substrate in Gas Turbine Blade

1995 ◽  
Author(s):  
Y. Sugita ◽  
M. Ito ◽  
N. Isobe ◽  
S. Sakurai ◽  
C. R. Gold ◽  
...  
Keyword(s):  
High Temperature ◽  
Gas Turbine ◽  
Cross Sections ◽  
Turbine Blades ◽  
Temperature Oxidation ◽  
Gas Turbine Blades ◽  
Coating Surface ◽  
Ductile Brittle Transition Temperature ◽  
Scanning Auger Microprobe ◽  
Long Time

This paper studied high temperature degradation behavior of gas turbine blades consisting of CoNiCrAlY coatings and Rene 80 substrates using a small punch (SP) testing technique at 295–1223 K and scanning Auger microprobe (SAM). In SP tests, coating cracks continuously propagated along the radial direction at 295 K and many cracks discretely were formed along more random directions at higher temperatures. The ductility of the coating at 295 K was reduced and the ductile-brittle transition temperature was increased during long time exposure of gas turbine blades to high temperature oxidation environments. SAM analyses on cross sections and fracture surfaces of the coatings indicated that oxidation and S segregation near the coating surface are profoundly induced in-service. The relationship between the mechanical properties and microstructural/chemical evolution near the coating surface is presented which serves as a data base for determining the remaining life of gas turbine blades.

scholarly journals High temperature fatigue testing of gas turbine blades

2017 ◽  
Vol 7 ◽  
pp. 206-213 ◽  
Author(s):  
M. Beghini ◽  
L. Bertini ◽  
C. Santus ◽  
B.D. Monelli ◽  
E. Scrinzi ◽  
...  
Keyword(s):  
High Temperature ◽  
Gas Turbine ◽  
Fatigue Testing ◽  
Turbine Blades ◽  
Gas Turbine Blades ◽  
High Temperature Fatigue

scholarly journals Assessment of Technical Condition Demonstrated by Gas Turbine Blades by Processing of Images for Their Surfaces / Oceny Stanu Łopatek Turbiny Gazowej Metodą Przetwarzania Obrazów Ich Powierzchni

2012 ◽  
Vol 21 (1) ◽  
pp. 41-50
Author(s):  
Józef Błachnio ◽  
Jarosław Spychała ◽  
Wojciech Pawlak ◽  
Artur Kułaszka
Keyword(s):  
High Temperature ◽  
Gas Turbine ◽  
Turbine Blades ◽  
Technical Condition ◽  
Test Method ◽  
Statistical Parameters ◽  
Gas Turbine Blades ◽  
First Order ◽  
Alloy Microstructure ◽  
Non Destructive

Abstract The paper presents a non-destructive test method that makes it possible to assess condition of gas turbine blades based on the analysis of their images acquired in visible light. The results of high temperature’s influence on the condition of blades are revealed. The direct relationship between the temperatures of blades and discoloration of their surfaces is demonstrated. These relationships have been found out by the analysis of images in the form of first order statistical parameters derived wherefrom. The studies revealed alterations of the blade superalloy microstructures entailed by the effect of high temperature, hence the results in the form of first order statistical parameters could be correlated against alterations of the blade superalloy microstructures. Eventually, the variations of first order statistical parameters as well as variations of the blade superalloy microstructures could be determined as the functions of temperature. These relationships make it possible to assess how much the alloy microstructure is altered due to high temperature merely by discoloration of the blade surface. The innovative method can be used for in-flight evaluation of the superalloy overheating for gas turbine blades in operation.

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