Engine Testing of Advanced Materials for Hypersonic Applications

2005 ◽  
Author(s):  
Michael J. Bur
Keyword(s):  
Rocket Engine ◽  
Ceramic Composites ◽  
Gaseous Hydrogen ◽  
Metal Alloys ◽  
Advanced Materials ◽  
Metallic Foams ◽  
Combustion Chambers ◽  
Hypersonic Propulsion ◽  
Engine Testing ◽  
Engine Components

This paper describes the use of a ground based gaseous hydrogen/oxygen rocket engine to test advanced materials for rocket engine and hypersonic propulsion applications. The types of materials that have been tested include ceramic composites, metallic alloys and ceramic and metallic foams. There are various configurations in which these materials can be tested. A “square” engine is used for testing flat rectangular panels by placing the panel downstream of the rocket nozzle in the exhaust path. A more traditional “round” rocket engine is used to test axisymmetric engine components such as nozzle inserts and combustion chambers that are fabricated from either ceramic composites or metal alloys. Besides hydrogen, other engine fuels such as methane are being evaluated in order to expose test materials to a hydrocarbon environment. Various organizations from industry, academia and other government agencies have used this test cell to facilitate the development of advanced materials for use in both rocket engine and hypersonic propulsion applications.

Biomimetic materials: An introduction

1992 ◽  
Vol 50 (2) ◽  
pp. 1020-1021 ◽  
Author(s):  
M. Sarikaya ◽  
J. T. Staley ◽  
I. A. Aksay
Keyword(s):  
Self Assembly ◽  
Structural Control ◽  
Hierarchical Structures ◽  
Ceramic Composites ◽  
Advanced Materials ◽  
Length Scale ◽  
Spider Webs ◽  
Biomimetic Materials ◽  
Synthetic Materials ◽  
All Ceramic

Biomimetics is an area of research in which the analysis of structures and functions of natural materials provide a source of inspiration for design and processing concepts for novel synthetic materials. Through biomimetics, it may be possible to establish structural control on a continuous length scale, resulting in superior structures able to withstand the requirements placed upon advanced materials. It is well recognized that biological systems efficiently produce complex and hierarchical structures on the molecular, micrometer, and macro scales with unique properties, and with greater structural control than is possible with synthetic materials. The dynamism of these systems allows the collection and transport of constituents; the nucleation, configuration, and growth of new structures by self-assembly; and the repair and replacement of old and damaged components. These materials include all-organic components such as spider webs and insect cuticles (Fig. 1); inorganic-organic composites, such as seashells (Fig. 2) and bones; all-ceramic composites, such as sea urchin teeth, spines, and other skeletal units (Fig. 3); and inorganic ultrafine magnetic and semiconducting particles produced by bacteria and algae, respectively (Fig. 4).

Ceramic Composites for Gas Turbine Engines via a New Process

1989 ◽  
Author(s):  
G. H. Schiroky ◽  
A. W. Urquhart ◽  
B. W. Sorenson
Keyword(s):  
Gas Turbine ◽  
Joint Venture ◽  
New Technology ◽  
Ceramic Composites ◽  
Gas Turbine Engine ◽  
Molten Metals ◽  
Oxidation Reactions ◽  
Turbine Engine ◽  
New Process ◽  
Engine Components

A new process for ceramic composites involves the growth of ceramic matrices through shaped preforms using directed oxidation reactions of molten metals. The preforms may consist of reinforcing fibers, whiskers, platelets, or particles, as needed to produce the desired properties in the finished component. This new technology is being developed by Lanxide Corporation and is being applied to gas turbine engine components by Du Pont Lanxide Composites Inc., a joint venture. The paper includes a description of the technology and a discussion of the status of its application to materials for gas turbine engine components.

scholarly journals Ceramic Composites for Rocket Engine Turbines

1991 ◽  
Author(s):  
Thomas P. Herbell ◽  
Andrew J. Eckel
Keyword(s):  
Rocket Engine ◽  
Ceramic Composites

Mechanical Response of Porous and Dense NiTi-TiC Composites

2004 ◽  
Vol 844 ◽  
Author(s):  
Douglas E. Burkes ◽  
Guglielmo Gottoli ◽  
John J. Moore ◽  
Reed A. Ayers
Keyword(s):  
Material Properties ◽  
Mechanical Response ◽  
Bulk Material ◽  
Processing Parameters ◽  
Ceramic Composites ◽  
Advanced Materials ◽  
Matrix Composites ◽  
Compression Tests ◽  
Commercial Applications ◽  
Micro Indentation

ABSTRACTThe Center for Commercial Applications of Combustion in Space (CCACS) at the Colorado School of Mines is currently using combustion synthesis to produce several advanced materials. These materials include ceramic, intermetallic, and metal-matrix composites in both porous and dense form. Currently, NiTi – TiC intermetallic ceramic composites are under investigation for use as a bone replacement material. The NiTi intermetallic has the potential to provide a surface that is capable of readily producing an oxide layer for corrosion resistance. The TiC ceramic has the potential to increase the hardness and wear resistance of the bulk material that can improve the performance lifetime of the implant. Processing parameters are critical to the production of the NiTi – TiC composite and will be discussed. These parameters can lead to the formation of substoichiometric TiC and nickel rich NiTi that changes the overall mechanical and material properties. In addition, the size of the TiC particles present within the bulk product varies with porosity. Both porous and dense samples have been mechanically analyzed employing micro-indentation techniques as well as compression tests in an attempt to characterize the mechanical response of these composites. The effects of the TiC particles, the formation of Ni3Ti intermetallic and the effects of porosity on the overall mechanical and material properties will be discussed.

Categorization of Human Errors in Rocket Engine Testing

1961 ◽  
Author(s):  
Lane B. Blank ◽  
Gustavus S. Miller
Keyword(s):  
Rocket Engine ◽  
Human Errors ◽  
Engine Testing

Advanced Materials for Mercury™ 50 Gas Turbine Combustion System

2006 ◽  
Author(s):  
Jeffrey Price ◽  
Josh Kimmel ◽  
Xiaoqun Chen ◽  
Arun Bhattacharya ◽  
Anthony Fahme ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Ceramic Matrix Composite ◽  
Field Evaluation ◽  
Ceramic Composites ◽  
Advanced Materials ◽  
Combustion System ◽  
Fuel Injector ◽  
Ods Alloys ◽  
Gas Turbine Combustion

Solar Turbines Incorporated (Solar), under cooperative agreement number DE-FC26-00CH 11049, is improving the durability of gas turbine combustion systems while reducing life cycle costs. This project is part of the Advanced Materials in Advanced Industrial Gas Turbines program in DOE’s Office of Distributed Energy. The targeted engine is the Mercury™ 50 gas turbine, which was developed by Solar under the DOE Advanced Turbine Systems (ATS) program (DOE contract number DE-FC21-95MC31173). The ultimate goal of the program is to demonstrate a fully integrated Mercury 50 combustion system, modified with advanced materials technologies, at a host site for 4,000 hours. The program has focused on a dual path development route to define an optimum mix of technologies for the Mercury 50 turbine and future Solar products. For liner and injector development, multiple concepts including high thermal resistance thermal barrier coatings (TBC), oxide dispersion strengthened (ODS) alloys, continuous fiber ceramic composites (CFCC), and monolithic ceramics were evaluated. An advanced TBC system for the combustor was down-selected for field evaluation. ODS alloys were down-selected for the fuel injector tip application. Preliminary component and sub-scale testing was conducted to determine material properties and demonstrate proof-of-concept. Full-scale rig and engine testing were used to validate engine performance prior to field evaluation. Field evaluation of ceramic matrix composite liners in the Centaur® 50 gas turbine engine [1–3] which was previously conducted under the DOE sponsored Ceramic Stationary Gas Turbine program (DE-AC02-92CE40960), is continuing under this program. This paper is a status review of the program, detailing the current progress of the development and field evaluations.

Advanced Composite Materials for Current and Future Propulsion and Industrial Applications

2006 ◽  
Vol 50 ◽  
pp. 174-181 ◽  
Author(s):  
Steffen Beyer ◽  
Stephan Schmidt ◽  
Franz Maidl ◽  
Rolf Meistring ◽  
Marc Bouchez ◽  
...  
Keyword(s):  
Composite Materials ◽  
Composite Structures ◽  
Chemical Vapour ◽  
Liquid Silicon ◽  
Large Temperature ◽  
Rocket Engines ◽  
Combustion Chambers ◽  
Standard Material ◽  
Liquid Rocket ◽  
Engine Components

Various technology programmes in Europe are concerned with preparing for future propulsion technologies to reduce the costs and increase the life time of components for liquid rocket engine components. One of the key roles to fulfil the future requirements and for realizing reusable and robust engine components is the use of modern and innovative materials. One of the key technologies which concern various engine manufacturers worldwide is the development of fibrereinforced ceramics – CMC's (Ceramic Matrix Composites). The advantages for the developers are obvious – the low specific weight, the high specific strength over a large temperature range, and their good damage tolerance compared to monolithic ceramics make this material class extremely interesting as a construction material. Different kind of composite materials are available and produced by EADS ST, the standard material SICARBON® (C/SiC made by Liquid Polymer Infiltration) and the new developed and qualified composite materials SICTEX® (C/SiC made by Liquid Silicon Infiltration) and CARBOTEX® (C/C made by Rapid Chemical Vapour Infiltration). The composites are based on textile techniques like weaving, braiding, stiching and sewing to produce multiaxial preforms, the SICTEX® material is densificated by the cost effective Liquid Silicon Infiltration (LSI). Over the past years, EADS Space Transportation (formerly DASA) has, together with various partners, worked intensively on developing components for airbreathing and liquid rocket engines. Since this, various prototype developments and hot firing-tests with nozzle extensions for upper and core stage engines and combustion chambers of satellite engines were conducted. MBDA France and EADS-ST have been working on the development of fuel-cooled composite structures like combustion chambers and nozzle extensions for future propulsion applications.

Zero-Emission MATIANT Cycle

1999 ◽  
Vol 121 (1) ◽  
pp. 116-120 ◽  
Author(s):  
P. Mathieu ◽  
R. Nihart
Keyword(s):  
Gas Turbines ◽  
Co2 Emission ◽  
Combustion Process ◽  
Advanced Materials ◽  
Working Fluid ◽  
Brayton Cycle ◽  
Combustion Chambers ◽  
Novel Technology ◽  
Technical Issues ◽  
Cycle Efficiency

In this paper, a novel technology based on the zero CO2 emission MATIANT (contraction of the names of the two designers MAThieu and IANTovski) cycle is presented. This latter is basically a gas cycle and consists of a supercritical CO2 Rankine-like cycle on top of regenerative CO2 Brayton cycle. CO2 is the working fluid and O2 is the fuel oxidizer in the combustion chambers. The cycle uses the highest temperatures and pressures compatible with the most advanced materials in the steam and gas turbines. In addition, a reheat and a staged compression with intercooling are used. Therefore, the optimized cycle efficiency rises up to around 45 percent when operating on natural gas. A big asset of the system is its ability to remove the CO2 produced in the combustion process in liquid state and at high pressure, making it ready for transportation, for reuse or for final storage. The assets of the cycle are mentioned. The technical issues for the predesign of a prototype plant are reviewed.

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