Experience With in 939 as a Hot Corrosion Resistant Turbine Vane Material

1984 ◽  
Author(s):  
Klaus Schneider ◽  
Roland Bauer ◽  
Marc Staubli ◽  
Hermann W. Grünling
Keyword(s):  
Hot Corrosion ◽  
Gas Turbines ◽  
Protective Coatings ◽  
Base Alloy ◽  
Corrosion Resistant ◽  
Term Operation ◽  
Actual Application ◽  
M Phase ◽  
Nickel Base ◽  
And Behavior

For stationary gas turbine vanes IN 939 was evaluated very thoroughly in Europe as a promising hot corrosion resistant nickel base alloy. This paper shows examples of properties and behavior of IN 939 from literature and from actual application in stationary gas turbines. After long-term operation in stationary gas turbines vanes are analysed to show the type of oxide scale formation, the hot corrosion attack and phase stability. The alloy IN 939 exhibited excellent hot corrosion resistance under severe environmental conditions comparable to that of commercial hot corrosion protective coatings. Phases are described developed after casting and during heat treatment and sensitivity towards M-phase formation is briefly discussed. Creep and fatique data of IN 939 are compared with IN 738 LC as well as the hot corrosion behavior.

WAUKESHA ALLOY 88

Alloy Digest ◽  
1993 ◽  
Vol 42 (2) ◽  
Keyword(s):  
Fracture Toughness ◽  
Stainless Steel ◽  
High Temperature ◽  
Physical Properties ◽  
Base Alloy ◽  
Heat Treating ◽  
Nickel Base Alloy ◽  
Corrosion Resistant ◽  
Temperature Performance ◽  
Nickel Base

Abstract WAUKESHA METAL NO. 88 is a corrosion resistant nickel-base alloy compounded to run against stainless steel without galling or seizing. This datasheet provides information on composition, physical properties, hardness, elasticity, and tensile properties as well as fracture toughness. It also includes information on high temperature performance as well as casting, heat treating, machining, and joining. Filing Code: Ni-84. Producer or source: Waukesha Foundry Company. Originally published July 1963, revised February 1993.

UDIMET 700

Alloy Digest ◽  
1987 ◽  
Vol 36 (1) ◽  
Keyword(s):  
Gas Turbines ◽  
Base Alloy ◽  
Heat Treating ◽  
Vacuum Arc ◽  
Vacuum Induction Melting ◽  
Induction Melting ◽  
Nickel Base Alloy ◽  
Vacuum Arc Remelting ◽  
Temperature Performance ◽  
Nickel Base

Abstract UDIMET 700 is a wrought nickel-base alloy produced by vacuum-induction melting and further refined by vacuum-arc remelting. It has excellent mechanical properties at high temperatures. Among its applications are blades for aircraft, marine and land-based gas turbines and rotor discs. This datasheet provides information on composition, physical properties, 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, joining, and surface treatment. Filing Code: Ni-51. Producer or source: Special Metals Corporation. Originally published March 1959, revised January 1987.

UDIMET 718

Alloy Digest ◽  
1978 ◽  
Vol 27 (11) ◽  
Keyword(s):  
Gas Turbines ◽  
Base Alloy ◽  
Heat Treating ◽  
High Yield ◽  
Nickel Base Alloy ◽  
Aged Condition ◽  
High Yield Strength ◽  
Unusual Combination ◽  
Critical Components ◽  
Nickel Base

Abstract UDIMET 718 is a nickel-base alloy that is precipitation hardenable. It exhibits exceptionally high yield strength up to 1300 F, excellent cryogenic properties down to -423 F and superior weldability even in the fully-aged condition. This unusual combination of characteristics makes it suitable for elevated-temperature applications in gas turbines and in critical components for missiles. This datasheet provides information on composition, physical properties, elasticity, and tensile properties as well as creep. It also includes information on forming, heat treating, machining, joining, and surface treatment. Filing Code: Ni-258. Producer or source: Special Metals Corporation.

The Effect of High Temperature on the Degradation of Heat-Resistant and High-Temperature Alloys

2009 ◽  
Vol 147-149 ◽  
pp. 744-751 ◽  
Author(s):  
Józef Błachnio
Keyword(s):  
High Temperature ◽  
Mechanical Strength ◽  
Gas Turbines ◽  
Base Alloy ◽  
Heat Resistant ◽  
High Temperature Materials ◽  
High Temperature Alloys ◽  
Aerospace Technology ◽  
Aero Engines ◽  
Nickel Base

Heat-resistant and high-temperature materials are used to manufacture components, devices, and systems operated at high temperatures, i.e. under severe heat loads. Gas turbines used in the power industry, the traction, marine, and aircraft engines, the aerospace technology, etc. are good examples of such systems. Generally, as the temperature increases, the mechanical strength of materials decreases. While making such materials, there is a tendency to keep possibly low thermal weakening. In the course of operating gas turbines, various kinds of failures/defects/ damages may occur to components thereof, in particular, to blades. Predominating failures/damages are those attributable to the material overheating and thermal fatigue, all of them resulting in the loss of mechanical strength. The paper has been intended to present findings on changes in the microstructure of blades made of nickel-base alloy due to high temperature. The material gets overheated, which results in the deterioration of the microstructure’s condition. The material being in such condition presents low high-temperature creep resistance. Any component, within which such an effect occurs, is exposed to a failure/damage usually resulting in the malfunctioning of the turbine, and sometimes (as with aero-engines) in a fatal accident. Failures/damages of this kind always need major repairs, which are very expensive.

Development of a Controlled-Expansion Superalloy for Use in Aircraft Gas Turbines

1995 ◽  
Author(s):  
James M. Dahl ◽  
John B. Hansen
Keyword(s):  
Gas Turbines ◽  
Room Temperature ◽  
Coefficient Of Thermal Expansion ◽  
Base Alloy ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Original Design ◽  
Nickel Base ◽  
Potential Customers ◽  
Selection Of

This paper describes the methodology employed to produce a controlled expansion superalloy that has been successfully incorporated in several advanced aircraft gas turbine engines. Objectives of the original R&D study are reviewed in light of requirements given by potential customers. Properties of the alloy are presented and compared to those objectives. It is reported that the alloy has mechanical properties similar to those of the nickel-base alloy 718, and a low coefficient of thermal expansion between room temperature and its Curie temperature of 320°C. It also reported that the alloy has sufficient oxidation resistance so it may be possible to use it uncoated to temperatures approaching 675°C. The selection of the alloy by engine producers is described and the reasons for selecting are noted to be different from the original design criteria.

NIMONIC ALLOY 901

Alloy Digest ◽  
1996 ◽  
Vol 45 (4) ◽  
Keyword(s):  
Fracture Toughness ◽  
High Temperature ◽  
Physical Properties ◽  
Gas Turbines ◽  
Rupture Strength ◽  
Base Alloy ◽  
Heat Treating ◽  
Nickel Base Alloy ◽  
Temperature Performance ◽  
Nickel Base

Abstract Nimonic alloy 901 is a nickel-base alloy strengthened by additions of molybdenum, titanium, and aluminum. It possesses high creep and rupture strength from 1000 to 1400 deg F. Applications include components for gas turbines, bolting, and valve stems for power applications. This datasheet provides information on composition, physical properties, elasticity, and tensile properties as well as fracture toughness and creep. It also includes information on high temperature performance as well as heat treating. Filing Code: Ni-339. Producer or source: Inco Alloys International Inc. Originally published September 1986, revised April 1996.

SANDVIK SANICRO 38/4L7

Alloy Digest ◽  
1996 ◽  
Vol 45 (8) ◽  
Keyword(s):  
Carbon Steel ◽  
Physical Properties ◽  
Base Alloy ◽  
Heat Treating ◽  
Nickel Base Alloy ◽  
Corrosion Resistant ◽  
Composite Tube ◽  
Nickel Base ◽  
Outside Diameter

Abstract Sandvik Sanicro 38/4L7 is a composite tube consisting of Sanicro 38, a corrosion-resistant nickel-base alloy on the outside diameter, and carbon steel (A210 GrA-1) for water-wetted service on the inside. The design is placed entirely on the inside tube; however, there is a contribution from both. This datasheet provides information on composition and physical properties. It also includes information on forming, heat treating, and joining. Filing Code: SA-483. Producer or source: Sandvik.

scholarly journals Repair Joints in Nickel-Based Superalloys With Improved Hot Corrosion Resistance

1993 ◽  
Author(s):  
K. A. Ellison ◽  
P. Lowden ◽  
J. Liburdi ◽  
D. H. Boone
Keyword(s):  
Hot Corrosion ◽  
Structural Changes ◽  
Base Alloy ◽  
Metallographic Analysis ◽  
Slight Reduction ◽  
Type I ◽  
Aluminide Coatings ◽  
Point Depressant ◽  
Identical Test ◽  
Nickel Base

Sample repair joints in the nickel-base superalloys Inconel IN-713 and IN-738 were tested in the laboratory for Type I high temperature hot corrosion (HTHC) resistance at 900°C. The joints were produced using a conventional “wide-gap” brazing process, having a composition similar to IN-718, and a novel powder metallurgy repair technique LPM™ which in this study had a composition similar to alloy IN-738. Metallographic analysis of the resulting structures showed that the IN-718 based repairs, with and without simple aluminide coatings, had suffered extensive intergranular attack of the braze joints. However, the HTHC resistance of cast IN-718 was found to be excellent under identical test conditions. A comparison of the uncoated LPM™ repair joints and cast IN-738 revealed only subtle differences in the morphology of the corrosion products; the maximum depths of attack were similar in each case. Silicon modified aluminide coatings provided a slight reduction in the rate of attack for the IN-738 alloy, while simple aluminide coatings were less resistant to HTHC than the base alloy. Similar results were found for the LPM™ joints, however localized coating penetration was observed in the vicinity of boride particles embedded in the coatings. These differences in behaviour were interpreted with reference to the chemical and structural changes brought about by the use of varying levels of boron as a melting point depressant in the repair layers.

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