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.

scholarly journals Ceramic Components for Automotive and Heavy Duty Turbine Engines: CATE and AGT 100

1982 ◽  
Author(s):  
H. E. Helms ◽  
J. A. Byrd
Keyword(s):  
Gas Turbine ◽  
Operating Time ◽  
Ceramic Materials ◽  
Turbine Engines ◽  
Aluminum Silicate ◽  
Lithium Aluminum ◽  
Gas Turbine Engines ◽  
Design Component ◽  
Controllable Factors ◽  
Ceramic Components

Detroit Diesel Allison is actively applying advanced ceramic materials to components in gas turbine engines. Silicon carbide, silicon nitride, aluminum silicate, lithium aluminum silicate, and mullite are materials being used in various components in both the DDA GT 404-4 and AGT 100 engines. Approximately 9400 hr of ceramic component operating time in the GT 404 engine has been accumulated, and design, component processing, proof testing, and engine testing experience have begun to show the applicability of ceramic materials in production engines. Material variability, processing procedures, strength characterization, and nondestructive evaluations are emerging as critical but controllable factors. Ceramic components offer the potential of significant fuel consumption improvements in gas turbine engines for vehicles and other applications.

Mechanical Attachment of Ceramics to Metals in Gas Turbine Engines

1993 ◽  
Author(s):  
J. Mark Battison
Keyword(s):  
Gas Turbine ◽  
Material Properties ◽  
Ceramic Materials ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Ceramic Component ◽  
Turbine Engine ◽  
Dynamic Components ◽  
Mechanical Attachment ◽  
Attachment Strategies

Williams International has been actively investigating the use of ceramic materials in gas turbine engines for over 10 years. Ceramic component applications include both static and dynamic components such as combustors and turbine rotors. Component stresses, material properties, and cost, dictate attachment strategies. Non-metallic turbines with metal-to-non-metallic attachment schemes have been successfully demonstrated. This paper reviews a progression of attachment strategies that eventually led to a successful test of a non-metallic turbine in a gas turbine engine.

Development and Investigation of Ceramic Parts for Gas-Turbine Engines

1997 ◽  
Author(s):  
Youry A. Nozhnitsky ◽  
Youlia A. Fedina ◽  
Anatoly D. Rekin ◽  
Nickolai I. Petrov
Keyword(s):  
Gas Turbine ◽  
Ceramic Materials ◽  
Mechanical Tests ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Metallic Materials ◽  
Turbine Engine ◽  
Protective Medium ◽  
Gas Generators ◽  
Engine Components

For years of time there have been conducted the investigations of gas-turbine engine parts made of carbon-carbon and ceramic materials. This paper presents mainly the results of works done to create engine components of ceramic materials. There are given the investigation results on development of equipment and methods intended for use in determining the characteristics of heat-resistant non-metallic materials under ultra high temperature conditions. The unique tooling is developed to be used for conducting mechanical tests in different conditions (vacuum, protective medium, air) at temperatures up to 2200°C. There are considered three possible fields of application of ceramic materials, that are, turbine (1), combustion chamber and other stator components operating at high temperatures (2), bearings (3). Different ceramic elements are designed and manufactured, their structural strength is investigated in the laboratory faculties and also as part of engine gas generators.

Materials requirements for high-temperature structures in the 21st century

1995 ◽  
Vol 351 (1697) ◽  
pp. 435-449 ◽  
Keyword(s):  
High Temperature ◽  
Gas Turbine ◽  
Intermetallic Compounds ◽  
21St Century ◽  
Ceramic Composites ◽  
Turbine Engines ◽  
Temperature Structure ◽  
Gas Turbine Engines ◽  
Technical Issues ◽  
Metal Polymer

The continued improvement in efficiency of high-temperature structures depends on improved materials and on designs that utilize these materials more effectively. This paper discusses the possibilities available to achieve these improvements. While the results are applicable to any high-temperature structure, the discussion focuses on gas turbine engines. This is because some of the most demanding requirements correspond to this application and the author is more familiar with this area. Possible materials can be separated into distinct classes: evolutionary and revolutionary materials. The former represent incrementally improved materials, mostly metals. The latter represent intermetallic compounds, and metal, polymer and ceramic composites. An attempt is made to estimate the extent of improvements that can be realized from each class of material. In addition, the barriers to realization of the gains are outlined. Where possible, next steps in overcoming these are described. Finally, non-technical issues such as material cost and availability are addressed and the growing importance of these factors is discussed.

scholarly journals Microwave Blade Tip Clearance Measurement System

1996 ◽  
Author(s):  
Richard Grzybowski ◽  
George Foyt ◽  
Hartwig Knoell ◽  
William Atkinson ◽  
Josef Wenger
Keyword(s):  
Gas Turbine ◽  
Measurement System ◽  
Ceramic Materials ◽  
Tip Clearance ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Phase Measurements ◽  
Blade Tip ◽  
Clearance Control ◽  
Blade Tip Clearance

This paper describes the development of a Microwave Tip Clearance Measurement System for use in the gas turbine environment Applications for this sensor include basic tip clearance measurements, seal wear measurement and active blade tip clearance control in gas turbine engines. The system being developed was designed for useful operation to temperatures exceeding 1093°F, since only ceramic materials are directly exposed in the gas path. Other advantages of this microwave approach to blade tip clearance sensing include the existence of an inherent self-calibration in the sensor that permits accurate operation despite temperature variations and possible abrasion by the rotating blades. Earlier experiments designed to simulate this abrasion of the sensor head indicated that rubs as deep as 1 mm (40 mils) were easily tolerated. In addition, unlike methods based upon phase measurements, this method is very insensitive to cable vibration and length variations. Finally, this microwave technique is expected to be insensitive to fuel and other engine contamination, since it is based on the measurement of resonant frequencies, which are only slightly affected by moderate values of loss due to contamination.

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.

The Application of Ceramics to the Small Gas Turbine

1970 ◽  
Author(s):  
A. F. McLean
Keyword(s):  
Gas Turbine ◽  
Lower Cost ◽  
Ceramic Materials ◽  
Turbine Engines ◽  
Inlet Temperature ◽  
Gas Turbine Engines ◽  
Turbine Inlet Temperature ◽  
Turbine Engine ◽  
Engine Components ◽  
Processing Techniques

This paper reviews the limitations today’s superalloys exercise on the realization of the potential of the gas turbine engine. Ceramic materials are suggested as a means of achieving lower cost and higher turbine inlet temperature in small gas turbine engines. The paper serves to introduce ceramic materials and processing techniques and identifies silicon nitride, silicon carbide and lithium-alumina-silicate as promising materials for high temperature turbine engine components.

Sign in / Sign up

Export Citation Format

Share Document