There the new equations of limiting states of turbine blades during the multifactor non-isothermal loading have been formulated and have been verified by experiment. The methodology member-by-member equivalent tests of turbine blades under the laboratory conditions has been developed. The methods have been developed, the technical facilities for the experimental study of strength characteristics of turbines during the isolated loading and during the multifactor loading have been created. The formation methods of programs of equivalent tests of turbine blades under the laboratory conditions have been developed. The methods of operational development of turbine blades according to the accuracy characteristics and to the life of present-day an...
The object of investigation: the most spread industry turbounits operating in combination with alter...
In view of the problem that the gas turbine blades rely more on the long-term test of the whole mach...
Diagnostics of the real state and residual life of the structural elements of an aircraft gas turbin...
The subject of this article is the methods of research and evaluation of the properties of turbine b...
The conditions leading to transfer of aircraft engines to "technical-condition" operation have been ...
The existing methods of evaluating turbine life, taking into account the effects of static and therm...
There the reliable design methods of main gasodynamical characteristics of blade lattices as well as...
In turbo jet engines, rotating discs are simultaneously subjected to mechanical and thermal loads. A...
A new approach to the analysis of the processes of propagation of fatigue cracks in the blades of ai...
The article examines the possibility of using converted aircraft engines for gas pumping units using...
In this thesis a test rig for blade life assessment has been designed. The test article is a blade f...
The aim of the present work was to develop a methodology for assessing reliability on the basis of p...
There the study objects are the turbine blades of GTE. The purpose is to develop the diagnostic tech...
The article deals with the problem of providing required gasdynamic and strength parameters of turbi...
There the main principles of thermal treatment of blades in the high-temperature alloys with coats h...
The object of investigation: the most spread industry turbounits operating in combination with alter...
In view of the problem that the gas turbine blades rely more on the long-term test of the whole mach...
Diagnostics of the real state and residual life of the structural elements of an aircraft gas turbin...
The subject of this article is the methods of research and evaluation of the properties of turbine b...
The conditions leading to transfer of aircraft engines to "technical-condition" operation have been ...
The existing methods of evaluating turbine life, taking into account the effects of static and therm...
There the reliable design methods of main gasodynamical characteristics of blade lattices as well as...
In turbo jet engines, rotating discs are simultaneously subjected to mechanical and thermal loads. A...
A new approach to the analysis of the processes of propagation of fatigue cracks in the blades of ai...
The article examines the possibility of using converted aircraft engines for gas pumping units using...
In this thesis a test rig for blade life assessment has been designed. The test article is a blade f...
The aim of the present work was to develop a methodology for assessing reliability on the basis of p...
There the study objects are the turbine blades of GTE. The purpose is to develop the diagnostic tech...
The article deals with the problem of providing required gasdynamic and strength parameters of turbi...
There the main principles of thermal treatment of blades in the high-temperature alloys with coats h...
The object of investigation: the most spread industry turbounits operating in combination with alter...
In view of the problem that the gas turbine blades rely more on the long-term test of the whole mach...
Diagnostics of the real state and residual life of the structural elements of an aircraft gas turbin...