REPAIR OF NOZZLE BLADES MADE OF HEAT-RESISTANT NICKEL ALLOY ZhS6U

2021 ◽  
pp. 3-13
Author(s):  
D.A. Dobrynin ◽  
◽  
M.S. Alekseeva ◽  
A.N. Afanasyev-Khodykin ◽  
◽  
...  
Keyword(s):  
Heat Treatment ◽  
Gas Turbine ◽  
State Of The Art ◽  
Hot Isostatic Pressing ◽  
Gas Turbine Engine ◽  
Structure And Properties ◽  
Turbine Engine ◽  
Repair Costs ◽  
Coating Methods ◽  
Gas Corrosion

An overview of traditional methods for cleaning the surface of gas turbine engine (GTE) blades from products of gas corrosion and spent coating, methods for restoring the structure and properties of the material of blades using hot isostatic pressing and heat treatment, as well as methods for applying coatings on the inner and outer surfaces of the blades is presented. The main disadvantages of these methods are described, taking into account which the state-of-the-art technology for repairing gas-turbine engine nozzle blades made of ZhS6U alloy has been developed in FSUE «VIAM», which ensures an increase in their resource and a reduction in repair costs.

Simple Instrumentation Rake Designs for Gas Turbine Engine Testing

1996 ◽  
Author(s):  
Peter D. Smout ◽  
Steven C. Cook
Keyword(s):  
Gas Turbine ◽  
Mechanical Damage ◽  
Engine Performance ◽  
Leading Edge ◽  
Gas Turbine Engine ◽  
Calibration Data ◽  
Turbine Engine ◽  
Industry Standard ◽  
Repair Costs ◽  
Engine Testing

The determination of gas turbine engine performance relies heavily on intrusive rakes of pilot tubes and thermocouples for gas path pressure and temperature measurement. For over forty years, Kiel-shrouds mounted on the rake body leading edge have been used as the industry standard to de-sensitise the instrument to variations in flow incidence and velocity. This results in a complex rake design which is expensive to manufacture, susceptible to mechanical damage, and difficult to repair. This paper describes an exercise aimed at radically reducing rake manufacture and repair costs. A novel ’common cavity rake’ (CCR) design is presented where the pressure and/or temperature sensors are housed in a single slot let into the rake leading edge. Aerodynamic calibration data is included to show that the performance of the CCR design under uniform flow conditions and in an imposed total pressure gradient is equivalent to that of a conventional Kiel-shrouded rake.

Development of the Centaur Type H Gas Turbine Engine

1985 ◽  
Author(s):  
G. L. Padgett ◽  
W. W. Davis
Keyword(s):  
Gas Turbine ◽  
High Efficiency ◽  
State Of The Art ◽  
Gas Turbine Engine ◽  
Development Plan ◽  
Inlet Temperature ◽  
Market Place ◽  
Turbine Inlet Temperature ◽  
Turbine Engine ◽  
Computer Aided

In response to the needs of the market place for turbines in the 5000 to 6000 hp class, Solar Turbines Incorporated has responded with an uprate of their Centaur engine. Discussed in this paper are the features of the uprated engine, the Development Plan and the methodology for incorporating into the design the advanced aerodynamic and mechanical technology of the Mars engine. The Mars engine is a high efficiency 12,500 hp engine which operates at a turbine inlet temperature of 1935°F. State-of-the-art computer aided methods have been applied to produce the design, and the results from this approach are displayed.

Near Net-Shape Forming of Thermal Barrier Coated Components for Gas Turbine Engine Applications

1998 ◽  
Author(s):  
G.E. Kim ◽  
P.G. Tsantrizos ◽  
S. Grenier ◽  
A. Cavasin ◽  
T. Brzezinski
Keyword(s):  
Mechanical Properties ◽  
Heat Treatment ◽  
Gas Turbine ◽  
Bond Coat ◽  
Gas Turbine Engine ◽  
Thermal Barrier ◽  
Forming Process ◽  
Turbine Engine ◽  
Near Net Shape ◽  
Net Shape Forming

Abstract PyroGenesis Inc. has developed a unique Vacuum Plasma Spraying (VPS) near-net-shape forming process for the production of multilayered free-standing components. Initial evaluation on the feasibility of applying this process for the production of gas turbine engine components has been performed. The VPS near-net-shape forming process consists of: selecting an appropriate mold material; preconditioning of mold surface ; depositing metallic, ceramic, or composite layers ; and removing mold from the spray-formed structure. The near-net-shape components are heat treated to improve their mechanical properties. A suitable heat treatment cycle was developed for the VPS-applied superalloy. Much of the recent improvements in gas turbine engine performance has been attributed to the introduction of thermal barrier coatings (TBC) for superalloy components. There exist, however, some limitations in current fabrication methods for closed hot-section components: less than ideal coating quality; welding; limited choice of superalloy material; etc... PyroGenesis has used VPS near-net-shape forming to fabricate closed components with an yttria-stabilized-zirconia inner layer, CoNiCrA1Y bond coat, and IN-738LC outer layer. The results from the initial study demonstrate the feasibility of producing near-net-shape components with good coating structures, superior superalloy materials, and the absence welds. The mold was reusable after minor surface conditioning. The TBC showed uniform thickness and microstructure with a smooth surface finish. The bond coat and structural superalloy layers were very dense with no signs of oxidation at the interface. After heat treatment, the mechanical properties of the IN-738LC compare favourably to cast materials.

scholarly journals The Low Emission Gas Turbine Passenger Car: What Does the Future Hold?

1973 ◽  
Author(s):  
T. F. Nagey ◽  
P. Mykolenko ◽  
M. E. Naylor ◽  
F. J. Verkemp
Keyword(s):  
Gas Turbine ◽  
State Of The Art ◽  
Gas Turbine Engine ◽  
Design Criteria ◽  
Passenger Cars ◽  
Passenger Car ◽  
Turbine Engine ◽  
Low Emission ◽  
The Future ◽  
Fundamental Design

This paper reviews the potential of the gas turbine as a low emission engine for passenger cars. State-of-the-art emission levels for turbines are identified together with the causes for the typically high levels of NOx that are encountered. Laboratory solutions for reduced NOx are discussed and some of the recent GM accomplishments defined. Fundamental design criteria for low emission combustors are identified. The paper concludes with a brief discussion of the problems remaining in the area of combustors for which solutions must be found before the gas turbine engine can be considered for general use.

The effect of diamond burnishing on structure and properties of detonation-gas coatings on gas-turbine engine parts

2008 ◽  
Vol 50 (1-2) ◽  
pp. 44-48 ◽  
Author(s):  
V. A. Boguslaev ◽  
V. K. Yatsenko ◽  
V. G. Yakovlev ◽  
L. P. Stepanova ◽  
G. V. Pukhal’skaya
Keyword(s):  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Structure And Properties ◽  
Turbine Engine ◽  
Diamond Burnishing

The Effect of Quenching Temperature on the Structure and Properties of Alloy Ei437B-VD Blades for a Helicopter Gas Turbine Engine

Metallurgist ◽  
2016 ◽  
Vol 60 (5-6) ◽  
pp. 617-621
Author(s):  
B. S. Lomberg ◽  
M. N. Letnikov ◽  
I. V. Kabanov ◽  
A. N. Chelombit’ko
Keyword(s):  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Structure And Properties ◽  
Quenching Temperature ◽  
Turbine Engine
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