Experimental industrial ion-plasma plants MESh-50 and MAP-R for applying protective coatings on transport and power gas turbine components

2021 ◽  
Author(s):  
S.A. Budinovskiy ◽  
A.A. Lyapin ◽  
A.S. Benklyan
Keyword(s):  
Gas Turbine ◽  
Protective Coatings ◽  
Operating Experience ◽  
Plasma Coating ◽  
Vacuum Arc ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Serial Production ◽  
Ion Plasma

The paper considers selected features of the protective ion-plasma coating deposition onto large-sized gas turbine components using vacuum-arc method by means of the MESh-50 and MAP-R pilot plants. The units have been developed based on the long-term operating experience of MAP-1 (MAP-1M) serial production. These plants are widely used in Russian and international aircraft-building complexes enabling all basic ion-plasma technological processes using standard cathodes made of nickel, cobalt, aluminum alloys and pure metals (Cu, Ti, Cr, Zr, etc.). The increased dimensions of the deposition chamber and the simultaneous use of several evaporators with pipe cathodes 180 mm in diameter and 540 mm high make it possible to apply coatings to large-sized components of gas turbine engines and plants, including such complex parts as “blisk” and “blink”.

scholarly journals HEAT AND EROSION-RESISTANT NANOSTRUCTURED COATINGS FOR GAS TURBINE ENGINES

Aviation ◽  
2013 ◽  
Vol 17 (4) ◽  
pp. 137-144 ◽  
Author(s):  
Aleksandrs Urbahs ◽  
Konstantins Savkovs ◽  
Margarita Urbaha ◽  
Kristine Carjova
Keyword(s):  
Gas Turbine ◽  
Oxidation Process ◽  
Sample Surface ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Functional Coatings ◽  
Temperature Oxidation ◽  
Plasma Sputtering ◽  
Ion Plasma ◽  
Basic Features

This work analyses the characteristics of functional coatings obtained by vacuum ion-plasma sputtering. These coatings have three-layer multiphase structure created as a result of condensing aluminium and titanium according to a certain programme. The article presents the results of investigation into the heat-resistance of ion-plasma coatings based on Ti-Al-N for titanium alloy parts of gas turbine engines. Analysis of the oxidation process between a sample surface and coatings within the range of 500–825 °C was carried out. The basic features of the process of coating destruction under high-temperature oxidation conditions were determined by means of scanning electron microscopy. The results of the tests made it possible to state that the coatings developed are able to operate at temperatures of 600–750 °C.

Evaluation of Heat-Resistant Alloys for Marine Gas Turbine Applications

1967 ◽  
Vol 89 (1) ◽  
pp. 23-27 ◽  
Author(s):  
L. J. Fiedler ◽  
R. M. N. Pelloux
Keyword(s):  
Gas Turbine ◽  
Protective Coatings ◽  
Test Facility ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
X Ray Diffraction ◽  
Combustion Gas ◽  
Turbine Engine ◽  
Gas Atmosphere ◽  
Combustion Residue

Materials for the turbine and combustor sections of gas turbine engines were evaluated for their resistance to sulfidation corrosion. The basic evaluation was conducted in a test facility by exposing the materials to a combustion gas atmosphere which simulates conditions of gas composition, corrosive combustion residue, gas velocity, and temperature that are encountered while operating a gas turbine engine in a marine environment. The influence of alloy composition, protective coatings, salt ingestion rates, and fuel sulfur content is discussed in relation to the degree of sulfidation corrosion. The mechanism of sulfidation corrosion attack, as determined by electron microprobe analyses and X-ray diffraction studies of corroded materials, is also discussed.

Fuel Problems With Marine Gas Turbine Engines

1967 ◽  
Author(s):  
J. P. Attiani
Keyword(s):  
Gas Turbine ◽  
Laboratory Tests ◽  
Operating Experience ◽  
Fuel Oil ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Test Program ◽  
Copper Deposits ◽  
Remedial Actions ◽  
Effect Of Copper

This paper describes a test program undertaken by the Navy to determine the causes of two problems in the fuel-oil systems of gas turbine engines. The first problem concerns short filter life; the second, copper deposits that cause clogging of fuel-oil nozzles. Results are given for operating experience with va-ious filter units from both laboratory tests and fleet experience. The effect of copper deposits on thermal stability is discussed. The author concludes with a review of remedial actions being taken to solve these problems.

The Potential Impact of Future Fuels on Small Gas Turbine Engines

1982 ◽  
Author(s):  
J. A. Saintsbury ◽  
P. Sampath
Keyword(s):  
Gas Turbine ◽  
Operating Experience ◽  
Gas Turbine Engine ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Turbine Engine ◽  
The Future ◽  
Potential Impact ◽  
The Impact ◽  
Whitney Aircraft

The impact of potential aviation gas turbine fuels available in the near to midterm, is reviewed with particular reference to the small aviation gas turbine engine. The future course of gas turbine combustion R&D, and the probable need for compromise in fuels and engine technology, is also discussed. Operating experience to date on Pratt & Whitney Aircraft of Canada PT6 engines, with fuels not currently considered of aviation quality, is reported.

scholarly journals Experimental Deposition of NaCl Particles From Turbulent Flows at Gas Turbine Temperatures

2019 ◽  
Vol 141 (2) ◽  
Author(s):  
Peter R. Forsyth ◽  
David R. H. Gillespie ◽  
Matthew McGilvray
Keyword(s):  
Gas Turbine ◽  
Turbulent Flows ◽  
Size Range ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Horizontal Pipe ◽  
Experimental Campaign ◽  
System Temperature ◽  
Secondary Air

The ingestion and deposition of solid particulates within gas turbine engines has become a very significant concern for both designers and operators in recent times. Frequently aircraft are operated in environments where sand, ash, dust, and salt are present, which can drive damage mechanisms from long term component degradation to in-flight flame-out. Experiments are presented to assess deposition characteristics of sodium chloride (NaCl) at gas turbine secondary air system temperature conditions in horizontal pipe flow. Monodisperse NaCl particles were generated in the size range 2.0–6.5 µm, with gas temperatures 390–480 °C, and metal temperatures 355–730 °C. Two engine-representative surface roughnesses were assessed. An experimental technique for the measurement of deposited NaCl based on solution conductivity was developed and validated. Experiments were carried out under isothermal and nonisothermal/thermophoretic conditions. An initial experimental campaign was conducted under ambient and isothermal conditions; high temperature isothermal results showed good similarity. Under thermophoretic conditions, deposition rates varied by up to several orders of magnitude compared to isothermal rates.

Gradient complex protective coatings for single-crystal turbine blades of high-heat gas turbine engines

2007 ◽  
Vol 49 (5-6) ◽  
pp. 253-259 ◽  
Author(s):  
V. P. Kuznetsov ◽  
V. P. Lesnikov ◽  
S. A. Muboyadzhyan ◽  
O. V. Repina
Keyword(s):  
Single Crystal ◽  
Gas Turbine ◽  
Protective Coatings ◽  
Turbine Blades ◽  
High Heat ◽  
Turbine Engines ◽  
Gas Turbine Engines

Preparation, Structure, and Properties of Ni3Al and NiAl Light Powder Alloys for Aerospace

2007 ◽  
Vol 534-536 ◽  
pp. 1585-1588 ◽  
Author(s):  
K.B. Povarova ◽  
O.A. Skachkov
Keyword(s):  
Gas Turbine ◽  
New Technology ◽  
Turbine Engines ◽  
Heat Sources ◽  
Gas Turbine Engines ◽  
Combustion Chambers ◽  
Term Operation ◽  
Heat Resistant ◽  
Turbine Installation

New light super-heat-resistant powder Ni3Al and NiAl-based alloys (of the Ni-Al-Mo-B, Ni-Al-Fe-La, and Ni-Al-Y2O3 systems), as well as a new technology for preparing and processing them have been developed. The density of the alloys was 7.3-7.5 and ~6 g/cm 3, respectively. The Ni3Al sheets were used to prepare shields for combustion chambers in gas-turbine engines by roomtemperature deformation; the shields are intended for the long-term operation at 1100-1200°C and for the short-term use at 1300°C. The activated NiAl powders alloyed with Fe+La were used to produce sintered complex-shape articles, such as combustion stabilizers in a jet unit of combustion chamber of the gas-turbine installation, heat sources, etc. capable of operating at t≤1500°C under low mechanical stresses. At 1100, 1300, and 1500°C, the 100-h strength of the heat-resistant NiAl- (2-7.5) vol. % Y2O3 alloys subjected to directional recrystallization is 70, 35 and ≥10 MPa, respectively. The vanes, in which the length of recrystallized grain is smaller than the vane length by a factor of 1.5-2, were manufactured from these alloys.

Long Term Thermal Stability of Several Gas Turbine Alloys

2005 ◽  
Author(s):  
L. M. Pike ◽  
S. K. Srivastava
Keyword(s):  
Mechanical Properties ◽  
Thermal Stability ◽  
Gas Turbine ◽  
Operating Costs ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Haynes 230 ◽  
One Year ◽  
Thermal Stability Of

Ever increasing demands for lower gas turbine operating costs have led to the need for longer lasting components. This in turn, requires the availability of alloys which are reliable to such long lifetimes. In the mill produced condition, most alloys have desirable microstructures and mechanical properties. However, after exposure to the harsh temperatures found in gas turbine engines, the microstructures of most alloys will begin to change. The effects on the mechanical properties of such microstructural changes can range from mild deterioration to significant degradation. In this paper, the effects of thermal exposures at temperatures from 1200 to 1600°F for durations up to one year on the mechanical properties of three wrought gas turbine alloys will be reported. The alloys will include HAYNES® 188 alloy (Co-Ni-Cr-W), HAYNES 230® alloy (Ni-Cr-W), and HAYNES HR-120® alloy (Fe-Ni-Cr-Nb-N).

Application of Ion-Plasma Coatings with Low Droplet Phase Content

2016 ◽  
Vol 870 ◽  
pp. 334-338 ◽  
Author(s):  
N.K. Krioni ◽  
A.D. Mingazhev ◽  
I.R. Kuzeev
Keyword(s):  
Protective Coatings ◽  
Plasma Coating ◽  
Electric Arc ◽  
Vacuum Arc ◽  
Coating Materials ◽  
Coating Application ◽  
Ion Plasma ◽  
Performance Reduction ◽  
Droplet Phase

Ion-plasma coating application technologies are the most advanced ones providing high performance characteristics for the parts of modern machinery and equipment. Further development of these technologies is connected with the improvement of efficiency, production processes, and quality of protective and strengthening coatings. The methods and installations for applying protective coatings by deposition of coating materials from vacuum arc plasma with the use of electric arc evaporators of metals are widely known. However, one of the main shortcomings of the existing technologies based on the use of electric arc evaporators is a high content of the droplet phase in the coating, resulting in a sharp performance reduction. In this paper, the authors propose a new approach to the process of ion-plasma material application, providing the implementation of a number of principles that improve the quality of the applied coating due to the significant reduction of the droplet phase.

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