GAS TURBINE ENGINES OVERHAUL
inspections
minor repair
major overhaul
medium overhaul
emergency repair
special repair
combustion chambers
combustion liners
nozzle assys
turbine rotor blades
DEFECTS FIDNING FOR HOT GAS PATH PARTS AND ASSYS
recovery OF HOT GAS PATH PARTS AND ASSYS
Aeroderivative gas turbine engines (AGTDs) are the most advanced within the typical range of power plant drives. Energy concentration per unit volume, at close to the maximum permissible values, operates in a lightweight gas turbine design, while the time between overhauls for AGTEs is, in some cases, twice that of industrial gas turbines.
These factors primarily impose the highest demands on materials and manufacturing technologies for assys and parts of aeroderivative gas turbines, and, consequently, the cost of their manufacture and reconditioning. Additionally, it's important to note the unique design features of this type of gas turbine engines, which include the fact, that some parts and assys of the AGTE have a limited life cycle, while similar parts found in industrial gas turbine engines have a significantly longer lifecycle.
AERODERIVATIVE GAS TURBINE ENGINES OVERHAUL
reconditioning of stator casings assys
reconditioning of compressors’ and turbines’ rotors
reconditioning of gearboxes and drive
reconditioning of linkage systems units
reconditioning of labyrinth seals of compressors’ & turbines’ rotors
reconditioning of shafts of compressors’ and turbines’ rotors
engineering preparation sequences for gas turbine engine parts castings
Casting wax model
Finished blade
Measurement check
Ceramic core
preparation activities
preparation activities
manufacturing activities
quality control activities
The degree of defectiveness of assys and parts determines the cost and time of refurbish, meanwhile, a proper examination of the found defects allows to select the suitable technology of the refurbishing of the assy/part. One of our company's services is the participation of our experts in defect finding processes as in the role of the Customer's representative.
дефектация бандажной полки рабочей лопатки турбины
Defect detection FOR HOT GAS PATH PARTS AND ASSYS
Prior to gas turbine engine overhaul, all assys and parts, which are subject to micrometric measurements for further calculations of clearances, alightings, etc., are listed within the refurbishment plan document.
micrometric measurements of assys and parts of gas turbine engines
TECHNOLOGY OF CLEANING OF GAS TURBINE ENGINE HOT PATH ASSYS AND PARTS
ABRASIVE TREATMENT
CHEMICAL STRIPPING
is processed in order to remove the formations, oxides, layers of previous coatings of parts/assys
THERMAL TREATMENT
is processed in order to control the remaining traces of old coatings (otherwise, if these are present, chipping will occur under the influence of high temperature)
When gas turbine hot section assys and parts are refurbished, special attention is paid to the surface preparation for the application of thermal barrier coatings. Properly prepared surfaces ensure high-quality adhesion between the blade alloy and the coating materials (particles).
THERMAL CLEANING
is processed in order to remove the oxides (thermal corrosion) off microcracks
is processed in order to remove the deposits, oxides, layers of previous coatings of cavities and holes of cooling system inner passages
The organization of the work of emergency commission for to detect the reasons of gas turbine engine emergency
INDEPENDENT EXPERTISE
AS IN ROLE OF CUSTOMER REPRESENTATIVE
DETERMICATION OF THE CAUSES OF GAS TURBINE EMERGENCY
The model ORM-65D liquid fuel rocket engine with a thrust of up to 1750 N, using nitric acid-kerosene fuel, was developed in 1936 under the leadership of Academician Valentin Petrovich Glushko. The engine was intended for installation on the RP-318 rocket plane and the 212 cruise missile designed by S.P. Korolev
The AM-3 (RD-3) turbojet engine specifically for the Tu-16 aircraft was developed in 1950 by Special Design Bureau-300 under the leadership of Alexander Alexandrovich Mikulin. The project was also known by the worktitle AMRD-03. At the time of its creation, it was the most powerful aircraft engine in the world.
The NK8 gas turbine engine successfully passed 100-hour state tests and was approved for the serial production at the Kuibyshev Engine Plant, named after M.V.Frunze, on December 25, 1954.
1936
1936
1947
1947
1952
1952
1956
1956
1950
1950
The Senior Founders of Russian turbomachinery industry
1954
1954
The first Soviet solid fuel jet engine was created, passing state tests in February 1947 under the leadership of Academician Arkhip Mikhailovich Lyulka. In subsequent years, a number of turbojet engines were developed under Arkhip Lyulka's team.
The modified VK-1A and VK-1F engines, using the method of boosting (increasing) thrust by burning fuel behind the turbine in the afterburner chamber, were built in 1952 under the leadership of Vladimir Yakovlevich Klimov.
The gas turbine units for the vehicles of naval forces of USSR serial production started at Southern turbine plant under the leadership of Chief Designer Sergey Dmitrievich Kolosov.
