Corrosion resistance of gas turbine blades tested in a high-temperature gas flow

1974 ◽  
Vol 6 (9) ◽  
pp. 1128-1131
Author(s):  
L. P. Lozitskii ◽  
E. N. Karpov ◽  
B. Ya. Kudryashov ◽  
N. N. Motrii
Keyword(s):  
Corrosion Resistance ◽  
High Temperature ◽  
Gas Turbine ◽  
Gas Flow ◽  
Turbine Blades ◽  
Gas Turbine Blades ◽  
High Temperature Gas

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.

scholarly journals ЭКСПЕРИМЕНТАЛЬНОЕ ИССЛЕДОВАНИЕ ВЛИЯНИЯ ТЕРМОИМПУЛЬСНОЙ ОБРАБОТКИ ЛОПАТОК ТУРБИН ГТД НА СКЛОННОСТЬ К ВЫСОКОТЕМПЕРАТУРНОЙ ГАЗОВОЙ КОРРОЗИИ

2018 ◽  
pp. 4-13
Author(s):  
Сергей Игоревич Планковский ◽  
Евгений Сергеевич Палазюк ◽  
Вадим Олегович Гарин ◽  
Юрий Вениаминович Дьяченко
Keyword(s):  
Corrosion Resistance ◽  
High Temperature ◽  
Turbine Blades ◽  
Corrosion Layer ◽  
Accelerated Tests ◽  
Thermal Pulse ◽  
Heat Resistant ◽  
Operational Characteristics ◽  
Gas Corrosion ◽  
High Temperature Gas

One of the most important parts of gas turbine engines (GTE) are turbine blades, because from their operational characteristics depend the maximum gas temperature in a turbine, its reliability and service life, specific power and economy of an engine. Different mechanical damages, cracks, traces of general corrosion, changing their working section, are unacceptable on blades. Analysis of main causes of the parts destruction in GTE flow section shows that in most cases formation of shearing distortions and cracks occurs on blades edges in the surface layer of material. The main reason for appearance of these defects are sulphide-oxide and high-temperature gas corrosion. The basic development tendencies of blades reliability increasing show, that together with the development of new heat-resistant alloys another possible way to prevent the destruction of blade material is increasing of blade manufacturing quality. The final shape of turbine blades is often achieved by machining, which leads to formation of burrs on the edges. Thermal pulse deburring has a large number of technological advantages and is the most promising method for finishing treatment of the surfaces and edges of GTE blades. However, despite the numerous positive examples of the application of laser treatment of blade surfaces in order to increase the corrosion resistance, the mechanism of phase and structural transformations, occurring in the surface layers of heat-resistant steels and alloys of different compositions, is still not fully understood. To estimate the effect of thermal pulse deburring of gas turbine blades on their operational characteristics, accelerated tests of blade specimens on the tendency to high-temperature gas corrosion have been carried out. The tests consist of sequential chemical etching in electrolyte, electrochemical treatment and high-temperature treatment in aggressive gases. These tests allow to obtain the same corrosion layer on blades surfaces, like after real operation. Also influence of laser deburring on corrosion resistance was estimated in parallel. The experimental study was carried out on the example of treatment of GTE nozzle blades made from a heat-resistant alloy on a nickel basis ZhS26-VI. Specimens were obtained by cutting two new blades into small parts by hydroabrasive cutting method to ensure that there is no thermal impact on the material being processed and no burn-out of the alloying elements. Obtained specimens of GTE blades after the cutting have been undergone by additional machining to obtain burrs at the edges, which were removed by thermal pulse and laser deburring methods. Investigation of the surface layer state of specimens after accelerated tests for high-temperature gas corrosion has been carried out by means of microscopic analysis. For this purpose, microslices of specimens have been prepared. Using a comparative analysis of the corrosion layer thickness after the tests, it was shown that there is no influence of thermal pulse and laser deburring methods on the tendency to high-temperature gas corrosion.

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.

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
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