scholarly journals Requirements for the order and the procedure of estimating structural strength characteristics of metal alloys for the main and critical parts of aviation gas turbine engines

2015 ◽  
Vol 14 (3-1) ◽  
pp. 37 ◽  
Author(s):  
Yu. A. Nozhnitsky ◽  
E. B. Kachanov ◽  
E. R. Golubovskiy ◽  
V. K. Kouevda
Keyword(s):  
Gas Turbine ◽  
Structural Strength ◽  
Metal Alloys ◽  
Strength Characteristics ◽  
Turbine Engines ◽  
Gas Turbine Engines

Multidisciplinary Design Optimization of a Bladed Disc for Small-Size Gas-Turbine Engines

2019 ◽  
Author(s):  
Anton Salnikov ◽  
Maxim Danilov
Keyword(s):  
Gas Turbine ◽  
Design Process ◽  
3D Model ◽  
Strength Characteristics ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Bladed Disks ◽  
Computational Region ◽  
Bladed Disk ◽  
Multidisciplinary Model

Abstract One of the most important units of small-size gas-turbine engines (GTE) is a turbine bladed disk, since it determines the total engine efficiency. Designing a turbine disks is a complex challenge due to the high loads and a large number of structural and technological constraints, as well as a variety of requirements to the bladed disks for small-size GTEs (higher efficiency, lower mass and adequate strength characteristics, etc.). Diverse requirements to the turbine bladed disks mean that modifying the structure in order to improve some characteristics will degrade other characteristics. A standard solution to this problem is to use the iterative approach, which reduces the design process to a consecutive iteration of setting and solving design problems concerning the bladed disk elements (blade and disk) separately for different aspects. The main drawback of this approach is its tremendous labor intensity and inferior quality of design, as this procedure does not consider the design object as a single entity. This paper proposes an approach to the turbine bladed disks design based on the use of a single multidisciplinary parametrized 3D model that contains several specialized submodels. These submodels define the essential computational regions, as well as the characteristics of the physical processes and phenomena in the object under study. The model also enables integration and interaction of the submodels in a single computational region. The single multidisciplinary model is modified and analyzed automatically, so the design problem is transformed into a multi-criteria optimization problem where the weight, gas dynamic and strength characteristics are used as criteria or constraints, and they are improved by varying the geometric parameters of the blade and disk. Each submodel simulates and analyzes the essential characteristics at the level comparable to the standard engineering calculations. Therefore, the designs obtained as a result of optimization do not need significant improvements, which facilitates and enhances the design process. The development of an integrated model is time consuming, but since the design and operation of bladed disks are similar, the created parametrized multidisciplinary 3D model can be used in the design of other similar disks after minor alternations taking into account the specifics of the new task.

Ceramic Micro Channel Recuperator Fabrication Methods for Small Gas Turbine Engines

2012 ◽  
Author(s):  
Matthew M. Kelly ◽  
Ming-Jen Pan ◽  
Sundar Atre ◽  
Gregory Rancourt ◽  
Andrew Heyes ◽  
...  
Keyword(s):  
High Temperature ◽  
Gas Turbine ◽  
Thermal Stresses ◽  
Fuel Efficiency ◽  
Ceramic Materials ◽  
Metal Alloys ◽  
Turbine Engines ◽  
Complex Structures ◽  
Gas Turbine Engines ◽  
Pressure Chemical

Recuperators can greatly improve the fuel efficiency of gas turbine engines, but they are normally heavy, bulky, expensive, and susceptible to high temperature creep, oxidation, and thermal stresses. One way to alleviate these problems is to make them from ceramic materials rather than metal alloys. However, fabricating these complex structures is a challenge. The technique investigated in this study was to laser-cut thin sheets of tapecast material into complex patterns, laminate them together into stacks, and sinter at high temperature. The layers were laminated together by applying heat, pressure, chemical solvents, and varying combinations of the three. This paper presents the results of all fabrication tests, describes the method used to successfully laminate and sinter one 33-layer stack, and summarizes other possible fabrication techniques for future investigation that would facilitate lamination the process.

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.

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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