Reliability and Durability of Ceramic Regenerators in a Gas Turbine

1978 ◽  
Vol 100 (1) ◽  
pp. 73-81 ◽  
Author(s):  
C. J. Rahnke ◽  
J. K. Vallance
Keyword(s):  
Thermal Stress ◽  
Gas Turbine ◽  
Mechanical Design ◽  
Ceramic Materials ◽  
Aluminum Silicate ◽  
Turbine Engine ◽  
Design Concepts ◽  
Chemical Attack ◽  
Magnesium Aluminum Silicate ◽  
Regenerator System

The two major causes of failure of ceramic regenerators in a gas turbine engine are excessive thermal stress and chemical attack of the basic ceramic material. Data are presented which show that regenerator life can be correlated on the basis of rim thermal-stress safety factor. Durability gains can be achieved through improved mechanical design of the regenerator system, as well as through improved ceramic materials. The test results from almost 50,000 hr of gas turbine operation on several different candidate materials and design concepts are also presented. Two materials, aluminum silicate and magnesium aluminum silicate, show promise of achieving the durability goals required for automotive and industrial turbine applications.

scholarly journals Development of a Low Thermal Expansion Magnesium-Aluminum-Silicate Ceramic for Gas Turbine Heat Exchanger Applications

1975 ◽  
Author(s):  
Sergej-Tomislav Buljan ◽  
R. N. Kleiner
Keyword(s):  
Thermal Expansion ◽  
Heat Exchanger ◽  
Gas Turbine ◽  
Ceramic Materials ◽  
Aluminum Silicate ◽  
Factors Influencing ◽  
Low Thermal Expansion ◽  
Magnesium Aluminum Silicate ◽  
Silicate Ceramic

A review of the factors influencing the thermal expansion of ceramic materials is presented. Studies have shown that thermal expansions lower than the theoretical value predicted for cordierite can be obtained. The properties of a low thermal expansion magnesium-aluminum-silicate ceramic developed for gas turbine heat exchanger applications are described.

scholarly journals 2MW Class High Efficiency Gas Turbine IM270 for Co-Generation Plants

1996 ◽  
Author(s):  
Hideo Kobayashi ◽  
Shogo Tsugumi ◽  
Yoshio Yonezawa ◽  
Riuzou Imamura
Keyword(s):  
Gas Turbine ◽  
High Efficiency ◽  
Mechanical Design ◽  
Development Program ◽  
Gas Turbine Engine ◽  
Maintenance Cost ◽  
Turbine Engine ◽  
Generation Plant ◽  
Emission Regulation ◽  
Heavy Duty Gas Turbine

IHI is developing a new heavy duty gas turbine engine for 2MW class co-generation plants, which is called IM270. This engine is a simple cycle and single-spool gas turbine engine. Target thermal efficiency is the higher level in the same class engines. A dry low NOx combustion system has been developed to clear the strictest emission regulation in Japan. All parts of the IM270 are designed with long life for low maintenance cost. It is planned that the IM270 will be applied to a dual fluid system, emergency generation plant, machine drive engine and so on, as shown in Fig.1. The development program of IM270 for the co-generation plant is progress. The first prototype engine test has been started. It has been confirmed that the mechanical design and the dry low NOx system are practical. The component tuning test is being executed. On the other hand, the component test is concurrently in progress. The first production engine is being manufactured to execute the endurance test using a co-generation plant at the IHI Kure factory. This paper provides the conceptual design and status of the IM270 basic engine development program.

scholarly journals Superhybrid Composite Blade Impact Studies

1981 ◽  
Vol 103 (4) ◽  
pp. 731-738 ◽  
Author(s):  
C. C. Chamis ◽  
R. F. Lark ◽  
J. H. Sinclair
Keyword(s):  
Structural Integrity ◽  
Mechanical Design ◽  
Impact Resistance ◽  
Leading Edge ◽  
Operating Conditions ◽  
Turbine Engine ◽  
Design Concepts ◽  
Composite Blade ◽  
Bird Impact ◽  
Small Bird

An investigation was conducted to determine the feasibility of superhybrid composite blades for meeting the mechanical design and impact resistance requirements of large fan blades for aircraft turbine engine applications. Two design concepts were evaluated: (1) leading edge spar (TiCom) and (2) center spar (TiCore), both with superhybrid composite shells. The investigation was both analytical and experimental. The results obtained show promise that superhybrid composites can be used to make light-weight, high-quality, large fan blades with good structural integrity. The blades tested successfully demonstrated their ability to meet steady-state operating conditions, overspeed, and small bird impact requirements.

scholarly journals Assessment of Mechanical Design Parameters for an Aero Gas Turbine Engine Jet Pipe Casing using Finite Element Analysis

2020 ◽  
Vol 9 (5) ◽  
pp. 1197-1201
Keyword(s):  
Finite Element Analysis ◽  
Finite Element ◽  
Gas Turbine ◽  
Mechanical Design ◽  
Three Dimensional ◽  
Gas Turbine Engine ◽  
Design Parameters ◽  
Element Analysis ◽  
Engine Operation ◽  
Turbine Engine

Aero Gas Turbine engines power aircrafts for civil transport application as well as for military fighter jets. Jet pipe casing assembly is one of the critical components of such an Aero Gas Turbine engine. The objective of the casing is to carry out the required aerodynamic performance with a simultaneous structural performance. The Jet pipe casing assembly located in the rear end of the engine would, in case of fighter jet, consist of an After Burner also called as reheater which is used for thrust augmentation to meet the critical additional thrust requirement as demanded by the combat environment in the war field. The combustion volume for the After burner operation together with the aerodynamic conditions in terms of pressure, temperature and optimum air velocity is provided by the Jet pipe casing. While meeting the aerodynamic requirements, the casing is also expected to meet the structural requirements. The casing carries a Convergent-Divergent Nozzle in the downstream side (at the rear end) and in the upstream side the casing is attached with a rear mount ring which is an interface between engine and the airframe. The mechanical design parameters involving Strength reserve factors, Fatigue Life, Natural Frequencies along with buckling strength margins are assessed while the Jet pipe casing delivers the aerodynamic outputs during the engine operation. A three dimensional non linear Finite Element analysis of the Jet pipe casing assembly is carried out, considering the up & down stream aerodynamics together with the mechanical boundary conditions in order to assess the Mechanical design parameters.

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.

scholarly journals Development of the Nissan YTP-12 Gas Turbine Engine

1976 ◽  
Author(s):  
Y. Sumi ◽  
S. Yamazaki ◽  
K. Kinoshita
Keyword(s):  
Gas Turbine ◽  
Mechanical Design ◽  
Engine Performance ◽  
Gas Turbine Engine ◽  
Durability Test ◽  
Turbine Engine ◽  
Component Test ◽  
Test Engine ◽  
Engine Development ◽  
Mechanical Arrangement

This paper describes the later progress of the Nissan YTP-12 gas turbine engine development. The mechanical design and the progress in its development are reviewed. The discussion includes mechanical arrangement, material, fuel control, major problems encountered and their solution. Component test, engine performance and durability test, and vehicle installation test are discussed briefly.

Methodology to Expedite Mechanical Component Design and Analysis in Gas Turbine Engines

2000 ◽  
Author(s):  
Ly D. Nguyen ◽  
Taison Ku
Keyword(s):  
Gas Turbine ◽  
Data Transfer ◽  
Mechanical Design ◽  
Computer Software ◽  
Turbine Engine ◽  
Analysis Process ◽  
Component Design ◽  
Cad Cam ◽  
Cyclic Symmetric ◽  
Engine Components

Abstract Advances in computer technology have enabled the utilization of sophisticated computer software to assist in mechanical design and analysis in various fields. CAD/CAM/CAE software, such as CATIA, UG (Unigraphic), CV (Computervision), ANSYS, NASTRAN, ABAQUS, Hypermesh and Tgrid, have proven to be effective tools for aiding designers and analysts. The challenges offered by these software improvements, are an efficient engineering design and analysis process, and the need for broader training of the designers and analysts conducting these processes. In the past these processes were often done sequentially and proved to be very time consuming. At Honeywell International Inc., a methodology has been established to synchronize CATIA®, CAD-fix®, ANSYS®, Hypermesh® and Tgrid® in the design and analysis of gas turbine engine components to speed the design analysis process. This paper describes the techniques used on such complex parts as the combustor case, the front frame support and the turbine nozzle to reduce cycle time in the design and analysis process. Modeling process techniques described in this paper include the implementation of cyclic symmetric boundary conditions, data transfer between CATIA and ANSYS using CAD-fix, and mesh control and sizing through the used of Hypermesh and Tgrid.

Design and Commissioning of an Engine-Like Test Environment

2013 ◽  
Author(s):  
Malcolm Laing ◽  
Todd Pickering ◽  
Dan Kominsky ◽  
Walter O’Brien ◽  
Steve Poland
Keyword(s):  
Gas Turbine ◽  
Development Program ◽  
Operating Regime ◽  
Test Rig ◽  
Test Environment ◽  
Turbine Engine ◽  
Design Concepts ◽  
Test And Evaluation ◽  
Engine Testing ◽  
Evaluation Platform

Test and evaluation are critical to any product development program. The validation of engine sensor products is particularly challenging since the test engine required for validation can range in value from thousands to millions of dollars, costing much more than the sensor product itself. As a result, significant sensor testing and validation is required by an engine owner prior to on-engine testing. To support our development activities and to facilitate test validation acceptance, we have created a test and evaluation platform for gas turbine sensors that will allow us to test developmental sensors in an engine-like environment without risking the possibility of engine damage. Driven by the core exhaust of a JT15-D engine, the Dynamic Rotor Research Rig (DR3) test and evaluation platform provides a test capability that is highly representative of the high temperatures, vibrations, gasses, fluids and overall gas turbine engine environment, while providing the means to easily add and replace sensors, add and test custom rotors, control temperature and rotor speeds, and to not risk engine health during test activities. Here we will discuss our sensor testing goals and how they fed into the operational goals and design considerations for the DR3. Early design concepts and the ultimate approach we took with the DR3 design will be explored, along with the candidate test rig component and subassembly fabrication processes that we evaluated and ultimately selected for use. We will review the manufacturing issues that we encountered during the construction phase of the DR3 and overview the commissioning of the DR3, problems that we discovered during start up and how we solved them. Included will be the results of initial turbine blade clearance and blade tip timing sensor testing performed on the DR3 and an evaluation of the DR3 performance, including temperature and speed control of the test rig and other characterization of the operating regime of the rig. Finally, we will present future plans to upgrade the DR3 rig to support future high temperature sensor and blade health monitoring development activities.

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