Author(s):  
T. B. Sweeting ◽  
F. J. Frechette ◽  
J. W. MacBeth

An update of the status of ceramic component development of the AGT Programs is presented. Activity on AGTO Program focussed on the following: successful transition from the prototype to engine configuration rotor, investigation of alternate rotor molding techniques, and completion of scroll assemblies. Progress on the Garrett AGT Program was highlighted by the introduction of plastic molding and extrusion to parts which were previously fabricated by slip casting and isopressing respectively.


1965 ◽  
Vol 8 (4) ◽  
pp. 33-46 ◽  
Author(s):  
Raymond Lekashman ◽  
John F. Stolle
Keyword(s):  

Author(s):  
B. J. McEntire ◽  
R. R. Hengst ◽  
W. T. Collins ◽  
A. P. Taglialavore ◽  
R. L. Yeckley ◽  
...  

Norton/TRW Ceramics (NTC) is performing ceramic component development as part of the DOE-sponsored Advanced Turbine Technology Applications Project (ATTAP). NTC’s work is directed at developing manufacturing technologies for rotors, stators, vane-seat platforms and scrolls. The first three components are being produced from a HIPed Si3N4, designated NT154. Scrolls were prepared from a series of siliconized silicon-carbide (Si-SiC) materials designated NT235 and NT230. Efforts during the first three years of this five-year program are reported. Developmental work has been conducted on all aspects of the fabrication process using Taguchi experimental design techniques. Appropriate materials and processing conditions were selected for powder beneficiation, densification and heat-treatment operations. Component forming has been conducted using thermal-plastic-based injection molding (IM), pressure slip-casting (PSC), and Quick-Set™ injection molding. An assessment of material properties for various components from each material and process were made. For NT154, characteristic room-temperature strengths and Weibull Moduli were found to be range between ≈920 MPa to ≈1 GPa and ≈10 to ≈19, respectively. Process-induced inclusions proved to be the dominant strength limiting defect regardless of the chosen forming method. Correction of the lower observed values is being addressed through equipment changes and upgrades. For the NT230 and NT235 Si-SiC, characteristic room-temperature strengths and Weibull Moduli ranged from ≈240 to ≈420 MPa, and 8 to 10, respectively. At 1370°C, strength values for both the HIPed Si3N4 and the Si-SiC materials ranged from ≈480 MPa to ≈620 MPa. The durability of these materials as engine components is currently being evaluated.


Author(s):  
R. S. Storm ◽  
R. G. Naum

An update on the status of ceramic component development in the AGT and CATE Programs will be presented. Activity on the DDA AGT Program has focused on injection molded rotors in addition to static components. Fabrication of components for the Garrett AGT Program emphasized the very large injection molded turbine shroud and injection molded interchangeable segmented stator as well as slip cast and isopressed components. The fabrication aspect of the CATE Turbine Blade Optimization Program will also be reviewed.


Author(s):  
Hamid Bagheri ◽  
Oscar Jimenez

Ceramics allow gas turbine engines to run at higher temperatures to increase power and efficiency. Ceramic component development is therefore required to understand transient thermal behavior and temperature distributions. As a part of contract with US Department of Energy (DOE), a series of finite element analyses were completed and a Solar Turbine (Solar) Centaur 50S engine was tested to characterize this behavior. To better understand the interaction between the metallic and ceramic components during engine operation, a finite element model was prepared. The boundary conditions for this model were estimated analytically or using existing test data. To verify the boundary conditions in the vicinity of uncooled ceramic components, two engine tests were performed on a metallic engine simulating the ceramic engine configuration. The Solar Centaur 50S engine normally operates at 1010°C with all metallic components. A Centaur 50S eagine was retrofitted with a ceramic combustor liner and uncooled first stage turbine blades and nozzles. Two tests were conducted at firing temperatures of 1095 and 980°C. Using metallic components saved time, reduced the complexity of working with ceramic components, and eliminated some of the difficulties of attaching instrumentation to ceramic parts. Component temperatures were measured and used in the finite element analyses to help predict blade tip clearances, ceramic component temperatures, stresses and ultimately component lives. The strategy undertaken and results presented herein provided a reliable and effective approach to ceramic component development and provides critical temperature information in the qualification process for ceramic gas turbines.


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