Computational and Experimental Investigation of Mechanical and Thermal Contacts of Ceramic Blades with the Metal Disk in Gas Turbine Engines

2018 ◽  
Vol 91 (6) ◽  
pp. 1365-1372 ◽  
Author(s):  
S. V. Reznik ◽  
D. V. Sapronov ◽  
P. V. Prosuntsov
Keyword(s):  
Experimental Investigation ◽  
Gas Turbine ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Metal Disk ◽  
Thermal Contacts

scholarly journals The Determination of Rational Parameters of Lock Joints of Ceramic Blades with a Metal Disk in Advanced Aircraft Gas Turbine Engines. Part I. Models of Mechanical and Thermal Contact of Ceramic and Metal Parts of the Turbine Impeller

2019 ◽  
pp. 71-81 ◽  
Author(s):  
S.V. Reznik ◽  
D.V. Sapronov ◽  
T.D. Karimbaev ◽  
M.A. Mezencev
Keyword(s):  
Tensile Strength ◽  
Gas Turbine ◽  
Thermal Contact ◽  
Metal Alloys ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Metal Parts ◽  
Metal Disk ◽  
Turbine Impeller

To increase the efficiency of aircraft gas turbine engines, it is necessary to increase the temperature of the gas before the turbine. However, metal alloys used in modern designs may not be used for this without a reduction in the durability of parts. One way to solve this problem is to develop turbine designs with ceramic elements. The issues of ensuring thermal resistance of the lock joints of turbine impellers with blades made of monolithic ceramic material are considered in this work. Models of mechanical and thermal contact of ceramic and metal parts are presented. The influence of the scale factor and stress concentration factor on the tensile strength of the ceramic parts is studied.

scholarly journals The Determination of Rational Parameters of Lock Joints of Ceramic Blades with a Metal Disk in Advanced Aircraft Gas Turbine Engines. Part II. Testing of the Rotor Model

2019 ◽  
pp. 76-84
Author(s):  
S.V. Reznik ◽  
D.V. Sapronov ◽  
T.D. Karimbaev ◽  
M.A. Mezencev
Keyword(s):  
Gas Turbine ◽  
Ceramic Materials ◽  
Ceramic Composites ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Lock Joint ◽  
Metal Disk ◽  
Operating Temperatures ◽  
Carbide Ceramics ◽  
Silicon Carbide Ceramics

The limited thermal stability of commonly used nickel alloys is an obstacle to further increases in operating temperatures in aircraft gas turbine engines. Alternative solutions that overcome the limitations of the operating temperatures of the gas in front of the turbine can be achieved using ceramic materials, including ceramic composites used for manufacturing blades and rotor. Due to a number of design and technological limitations associated with the production of fully ceramic parts of gas turbine engines, the option of connecting metal impellers with blades made of monolithic ceramic material deserves attention. A design of a model steel impeller with blades made of silicon carbide ceramics with reinforcing diamond particles is proposed. To determine the bearing capacity of the ‘dovetail’ type lock joint, bench tests were carried out. A computer program for probabilistic evaluation of the strength of ceramic parts is developed. A conclusion is made about the required characteristics of ceramic materials for the use in turbine impellers.

Gas Screen in Components of Gas Turbine Engines

1997 ◽  
Vol 28 (7-8) ◽  
pp. 536-542
Author(s):  
A. A. Khalatov ◽  
I. S. Varganov
Keyword(s):  
Gas Turbine ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Gas Screen

Potential Application of Composite Materials to Future Gas Turbine Engines

1988 ◽  
Author(s):  
James C. Birdsall ◽  
William J. Davies ◽  
Richard Dixon ◽  
Matthew J. Ivary ◽  
Gary A. Wigell
Keyword(s):  
Composite Materials ◽  
Gas Turbine ◽  
Potential Application ◽  
Turbine Engines ◽  
Gas Turbine Engines

Method of tribodiagnostics of d-30KU engines/KP with the use of a microwave plasma complex: results of metrological examination and analysis of the accuracy

2020 ◽  
pp. 22-29
Author(s):  
A. Bogoyavlenskiy ◽  
A. Bokov
Keyword(s):  
Gas Turbine ◽  
Microwave Plasma ◽  
Technical Condition ◽  
The State ◽  
Turbine Engines ◽  
Metrological Examination ◽  
Gas Turbine Engines ◽  
High Frequency Plasma ◽  
Frequency Plasma ◽  
Primary Standards

The article contains the results of the metrological examination and research of the accuracy indicators of a method for diagnosing aircraft gas turbine engines of the D30KU/KP family using an ultra-high-frequency plasma complex. The results of metrological examination of a complete set of regulatory documents related to the diagnostic methodology, and an analysis of the state of metrological support are provided as well. During the metrological examination, the traceability of a measuring instrument (diagnostics) – an ultrahigh-frequency plasma complex – is evaluated based on the scintillation analyzer SAM-DT-01–2. To achieve that, local verification schemes from the state primary standards of the corresponding types of measurements were built. The implementation of measures to eliminate inconsistencies identified during metrological examination allows to reduce to an acceptable level the metrological risks of adverse situations when carrying out aviation activities in industry and air transportation. In addition, the probability of occurrence of errors of the first and second kind in the technological processes of tribodiagnostics of aviation gas turbine engines is reduced when implementing a method that has passed metrological examination in real practice. At the same time, the error in determining ratings and wear indicators provides acceptable accuracy indicators and sufficient reliability in assessing the technical condition of friction units of the D-30KP/KP2/KU/KU-154 aircraft engines.

On the prospects of application of nanostructured heterophase polyfunctional composite materials inengine building industry

2019 ◽  
pp. 50-57
Author(s):  
O. B. Silchenko ◽  
M. V. Siluyanova ◽  
V. Е. Nizovtsev ◽  
D. A. Klimov ◽  
A. A. Kornilov
Keyword(s):  
Composite Materials ◽  
Gas Turbine ◽  
Developed Countries ◽  
The United States ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Nanostructured Composite ◽  
Polymer Metal ◽  
Long Operation ◽  
Prospects Of Application

The paper gives a brief review of properties and applications of developed extra-hard nanostructured composite materials and coatings based on them. The presentresearch suggestsaerospace applications of nanostructured composite materials based on carbides, carbonitrides and diboridesof transition and refractory metals. To improve the technical and economic performance of gas turbine engines, it is advisable to use new composite structural materials whose basic physicomechanical properties are several times superior to traditional ones. The greatest progress in developing new composites should be expected in the area of materials created on the basis of polymer, metal, intermetallic and ceramic matrices. Currently components and assemblies of gas turbine engines and multiple lighting power units with long operation life and durability will vigorously develop. Next-generation composites are studied in all developed countries, primarily in the United States and Japan.

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