Metallurgy of High-Temperature Alloys Used on Current Gas Turbine Designs

2009 ◽  
pp. 99-99-14 ◽  
Author(s):  
F. S. Badger ◽  
W. O. Sweeny
Keyword(s):  
High Temperature ◽  
Gas Turbine ◽  
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

High-temperature Alloys in Relation to Gas-turbine Design

1952 ◽  
Vol 166 (1) ◽  
pp. 123-130
Author(s):  
K. L. Buckle
Keyword(s):  
Heat Treatment ◽  
High Temperature ◽  
Gas Turbine ◽  
Temperature Effects ◽  
Material Selection ◽  
Combustion Chambers ◽  
New Approach ◽  
High Temperature Alloys ◽  
Component Design ◽  
Turbine Design

In order to achieve a thermal efficiency in the gas turbine comparable with that realized in steam practice, a higher turbine-entry temperature is necessary. Limiting discussion to the combustion and expansion sections of the gas turbine, the paper first indicates that the use of metals in high temperature and stress conditions necessitates a new approach to component design. The phenomena of creep and fatigue assume major importance whilst pure temperature effects, such as expansion and thermal shock, are additional problems. These properties are defined and an indication is given of their significance in the design of combustion chambers, turbine wheels, and blades. Susceptibility to heat treatment, intended to induce the desired high-temperature properties, is another important factor to be considered in material selection, as are fabrication characteristics. Since the latter govern both detail and general design, the merits of forging, casting, and welding are outlined when applied to high-temperature alloys. The paper concludes with a survey of the problems likely to be encountered with future materials, particularly ceramics, whilst suggesting that increased efficiency may be obtained by further research on established alloys or by design innovations such as cooling.

The Problem of High Temperature Alloys for Gas Turbines

1948 ◽  
Vol 52 (445) ◽  
pp. 1-26
Author(s):  
William T. Griffiths
Keyword(s):  
High Temperature ◽  
Gas Turbine ◽  
High Temperatures ◽  
Gas Turbines ◽  
High Speed ◽  
Mechanical Equipment ◽  
Aircraft Engines ◽  
Efficient Operation ◽  
High Temperature Alloys

It is now a matter of history that the development of an efficient gas turbine for use in aircraft engines had to await the availability of materials with the properties which would give an adequate life under the conditions which have to be imposed for efficient and economic service. These conditions are, of their type, more severe than any so far imposed on materials in other mechanical equipment. For efficient operation the gases employed in the turbine must be at a high temperature and the flow of gas passing through must be large. In aircraft engines also, the turbine must operate at high speed, with the resulting accompaniment of high stresses. It was to the metallurgist that the engineer naturally turned first for materials to meet these conditions of high temperatures and high stresses and, although some attention has been given to non-metallic substances, the problem still remains essentially a metallurgical one.

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.

CM-R 411

Alloy Digest ◽  
1967 ◽  
Vol 16 (9) ◽  
Keyword(s):  
Shear Strength ◽  
High Temperature ◽  
Gas Turbine ◽  
Precipitation Hardening ◽  
Base Alloy ◽  
Heat Treating ◽  
Nickel Base Alloy ◽  
Jet Engine ◽  
Temperature Performance ◽  
Nickel Base

Abstract CM-R41 is a vacuum-melted, precipitation hardening nickel-base alloy possessing outstanding properties in the temperature range of 1200 F to 1800 F. It is recommended for jet engine and gas turbine components operating at high temperatures. This datasheet provides information on composition, physical properties, elasticity, tensile properties, and shear strength as well as creep. It also includes information on high temperature performance as well as forming, heat treating, machining, and joining. Filing Code: Ni-127. Producer or source: Cannon-Muskegon Corporation.

CARPENTER M-252

Alloy Digest ◽  
1973 ◽  
Vol 22 (9) ◽  
Keyword(s):  
Corrosion Resistance ◽  
High Temperature ◽  
Physical Properties ◽  
Gas Turbine ◽  
Base Alloy ◽  
Heat Treating ◽  
Nickel Base Alloy ◽  
Jet Engine ◽  
Temperature Performance ◽  
Nickel Base

Abstract CARPENTER M-252 is an age-hardenable nickel-base alloy designed for highly stressed parts operating at temperatures up to 1600 F. Its prime application is for jet-engine and gas-turbine buckets. This datasheet provides information on composition, physical properties, hardness, elasticity, and tensile properties as well as creep. It also includes information on high temperature performance and corrosion resistance as well as forming, heat treating, machining, and joining. Filing Code: Ni-195. Producer or source: Carpenter.

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