scholarly journals DETERMINATION OF RUPTURE SOURCES OF TURBINE BLADE PACKETS AT PERFORMANCE OF FORENSIC EXAMINATIONS

2017 ◽  
Vol 17 ◽  
pp. 297-307
Author(s):  
A. V. Rusanov ◽  
G. Yu. Martynenko ◽  
K. V. Avramov ◽  
V O. Varlahov ◽  
V. G. Martynenko
Keyword(s):  
Gas Dynamics ◽  
Strain State ◽  
Turbine Blades ◽  
Dynamic Strength ◽  
Dynamic Loads ◽  
Applied Physics ◽  
Stress Strain ◽  
Bladed Disk ◽  
Stress Strain State ◽  
Gas Dynamic

The technique ofdetermination of rupture sources of the turbine blades packets, which can be used at performance of forensic expertise is suggested. Its distinctive feature is completeness of the account of the various factors concerning different areas of the applied physics, such as gas dynamics, heat conductivity, thermoelasticity, static and dynamic strength. The following series of calculations was made for acknowledgement of rupture sources of bladed disk. I. Calculation of a viscous compressed subsonic current. II. Calculation periodic gas-dynamic loads operating on the blades. III. Calculation of a non-stationary stress-strain state of the bladed disk under the action of periodic forces. The technique is based on use of the numerical methods of gas dynamics and dynamic strength. The steam current through a turbomachine step calculated with the help of model of the viscous, compressedfluid. The forced vibrations of the bladed disk under the action of the aerodynamic loads are analyzed by the numerical integration of the nonlinearfinite elements design model. Four cases are considered for the numerical calculations of the stress-strain state. I. The clearance in the disk slots are not accounted and the vibrations under the action ofgas-dynamic loads from ideal directing device are investigated. II. The clearance in the disk slots are not accounted and the vibrations under the action of gas- dynamic loads from defective directing device are investigated. III. The clearance in the disk slots are taken into account and the vibrations under the action of gas-dynamic loads from ideal directing device are investigated. IV. The clearance in the disk slots are taken into account and the vibrations under the action of gas-dynamic loads from defective directing device are investigated. It’s established that a source of rupture ofworking blades of a regulating step of a compartment of a high pressure of the steam turbine is damage of blades of the directing device.

scholarly journals Stress-strain state of brickwork under the action of static and dynamic loads

2019 ◽  
Vol 9 (1) ◽  
pp. 38-49
Author(s):  
Ilya N. Arkhipov ◽  
◽  
Vladimir I. Palagushkin ◽  
Nikolay I. Marchuk ◽  
Inna Ya. Petukhova ◽  
...  
Keyword(s):  
Strain State ◽  
Dynamic Loads ◽  
Stress Strain ◽  
Stress Strain State ◽  
Static And Dynamic Loads

Using FEM Analysis for Evaluating Lifetime of the Turbine Blades Repaired by Different Kinds of Titanium and Nickel Alloys

2008 ◽  
Vol 47-50 ◽  
pp. 37-40
Author(s):  
Aleksandrs Korjakins ◽  
Sergejs Gluhihs ◽  
Andrejs Popovs ◽  
Aleksandr Tiskunov
Keyword(s):  
Strain State ◽  
Turbine Blades ◽  
Fem Analysis ◽  
Laser Forming ◽  
Stress Strain ◽  
Element Analysis ◽  
Stress Strain State ◽  
Wide Range ◽  
Direct Laser ◽  
Attractive Option

With increasing attention being devoted to the problem of reducing service costs for a wide range of turbines and compressors, an attractive option is repair of damaged blades, instead of replacing them by new ones. A lot of different methods are used to repair blades and other parts of turbines and compressors. The processes of laser metal deposition (LMD) and direct laser forming (DLF) are modern methods used to repair blades made of titanium alloys. In the present study, the finite element analysis (FEM) has been applied to determine the stress-strain state of the repaired blades in service conditions. Different forms and sizes of the damaged zones have been analyzed. Several kinds of alloys, such as Incoloy 903, Carlson C800 and Inconel 718, appropriate for the LMD and DLF methods, have been utilized in repairing the blades. Two kinds of blades, with and without cooling hollows, have been examined. Lifetime of the repaired turbine has been evaluated by comparing the results obtained from the modal and stress-strain state analyses of the repaired and original parts. The results allow evaluating influence of sizes and forms of the damaged zones, as well as choice of the alloys applied, on lifetime of the repaired blades.

Stress-strain state of Francis turbine blades

1981 ◽  
Vol 15 (12) ◽  
pp. 755-762
Author(s):  
I. P. Ivanchenko ◽  
L. L. Smelkov ◽  
T. E. Pupko ◽  
A. Ya. Timashkov ◽  
B. K. Vapnik
Keyword(s):  
Strain State ◽  
Turbine Blades ◽  
Francis Turbine ◽  
Stress Strain ◽  
Stress Strain State

scholarly journals DYNAMIC STRENGTH CONDITION OF CONCRETE UNDER PLANE STRESS STATE

2019 ◽  
Vol 21 (4) ◽  
pp. 138-145
Author(s):  
Z. R. Galyautdinov
Keyword(s):  
Reinforced Concrete ◽  
Stress State ◽  
Plane Stress ◽  
Strain State ◽  
Dynamic Deformation ◽  
Dynamic Strength ◽  
Strength Condition ◽  
Stress Strain ◽  
Stress Strain State ◽  
Wide Range

Modern calculation models must take into account the dynamic deformation of reinforced concrete. Currently, the main regularities of nonlinear dynamic deformation of reinforced concrete under uniaxial stress state are theoretically analyzed in detail along with a wide range of experimental studies. Properties of concrete under plane stress -strain state and dynamic loading are examined to a lesser extent. This paper proposes the dynamic strength condition for the concrete strength which allows for changing the strain -hardening coefficient of concrete depending on the type of stress -strain state, the ratio of the primary stresses and the deformation rate.

КОНСТРУКТИВНО-ТЕХНОЛОГІЧНІ ОСОБЛИВОСТІ ХВОСТО-ВИХ БАЛОК СІТЧАСТОГО ТИПУ З ПОЛІМЕРНИХ КОМПО-ЗИЦІЙНИХ МАТЕРІАЛІВ ВЕРТОЛЬОТІВ ТРАНСПОРТНОЇ КАТЕГОРІЇ

2020 ◽  
pp. 15-30
Author(s):  
А. Г. Гребеников ◽  
И. В. Малков ◽  
В. А. Урбанович ◽  
Н. И. Москаленко ◽  
Д. С. Колодийчик
Keyword(s):  
Finite Element ◽  
Strain State ◽  
Layer Structure ◽  
Metal Structure ◽  
Element Model ◽  
Stress Strain ◽  
Element Analysis ◽  
Mesh Structure ◽  
Stress Strain State ◽  
Mesh Structures

The analysis of the design and technological features of the tail boom (ТB) of a helicopter made of polymer composite materials (PCM) is carried out.Three structural and technological concepts are distinguished - semi-monocoque (reinforced metal structure), monocoque (three-layer structure) and mesh-type structure. The high weight and economic efficiency of mesh structures is shown, which allows them to be used in aerospace engineering. The physicomechanical characteristics of the network structures are estimated and their uniqueness is shown. The use of mesh structures can reduce the weight of the product by a factor of two or more.The stress-strain state (SSS) of the proposed tail boom design is determined. The analysis of methods for calculating the characteristics of the total SSS of conical mesh shells is carried out. The design of the tail boom is presented, the design diagram of the tail boom of the transport category rotorcraft is developed. A finite element model was created using the Siemens NX 7.5 system. The calculation of the stress-strain state (SSS) of the HC of the helicopter was carried out on the basis of the developed structural scheme using the Advanced Simulation module of the Siemens NX 7.5 system. The main zones of probable fatigue failure of tail booms are determined. Finite Element Analysis (FEA) provides a theoretical basis for design decisions.Shown is the effect of the type of technological process selected for the production of the tail boom on the strength of the HB structure. The stability of the characteristics of the PCM tail boom largely depends on the extent to which its design is suitable for the use of mechanized and automated production processes.A method for the manufacture of a helicopter tail boom from PCM by the automated winding method is proposed. A variant of computer modeling of the tail boom of a mesh structure made of PCM is shown.The automated winding technology can be recommended for implementation in the design of the composite tail boom of the Mi-2 and Mi-8 helicopters.

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