SNECMA Experience With Cost-Effective DS Airfoil Technology Applied Using CM 186 LC® AlloySource: Journal of Engineering for Gas Turbines and Power:;1998:;volume( 120 ):;issue: 001::page 97Author:F. Caruel
,
K. Harris
,
G. L. Erickson
,
S. Bourguignon
,
B. Lallement
,
J. B. Wahl
,
S. Fargeas
,
A. DeBussac
DOI: 10.1115/1.2818093Publisher: The American Society of Mechanical Engineers (ASME)
Abstract: From a cost point of view SNECMA has found DS columnar grain manufacturing technology to be highly attractive compared to single crystal. CM 186 LC alloy exhibits enhanced mechanical and environmental properties and temperature capability compared to MAR M 200 Hf alloy; these properties are close to first-generation single crystal alloys up to 982°C (1800°F). The alloy is shown to be amenable to various coating and brazing high-temperature processes. The longer term creeprupture/phase stability data base on the alloy has now been extended out to 8300 hours at 1038°C (1900°F). Castings for engine test have been produced using CM 186 LC alloy.
keyword(s): Alloys , Airfoils , Crystals , Coating processes , Coatings , Stability , Temperature , Engines , Brazing , Manufacturing technology , Databases AND High temperature ,
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| contributor author | F. Caruel | |
| contributor author | K. Harris | |
| contributor author | G. L. Erickson | |
| contributor author | S. Bourguignon | |
| contributor author | B. Lallement | |
| contributor author | J. B. Wahl | |
| contributor author | S. Fargeas | |
| contributor author | A. DeBussac | |
| date accessioned | 2017-05-08T23:56:39Z | |
| date available | 2017-05-08T23:56:39Z | |
| date copyright | January, 1998 | |
| date issued | 1998 | |
| identifier issn | 1528-8919 | |
| identifier other | JETPEZ-26775#97_1.pdf | |
| identifier uri | http://yetl.yabesh.ir/yetl/handle/yetl/120471 | |
| description abstract | From a cost point of view SNECMA has found DS columnar grain manufacturing technology to be highly attractive compared to single crystal. CM 186 LC alloy exhibits enhanced mechanical and environmental properties and temperature capability compared to MAR M 200 Hf alloy; these properties are close to first-generation single crystal alloys up to 982°C (1800°F). The alloy is shown to be amenable to various coating and brazing high-temperature processes. The longer term creeprupture/phase stability data base on the alloy has now been extended out to 8300 hours at 1038°C (1900°F). Castings for engine test have been produced using CM 186 LC alloy. | |
| publisher | The American Society of Mechanical Engineers (ASME) | |
| title | SNECMA Experience With Cost-Effective DS Airfoil Technology Applied Using CM 186 LC® Alloy | |
| type | Journal Paper | |
| journal volume | 120 | |
| journal issue | 1 | |
| journal title | Journal of Engineering for Gas Turbines and Power | |
| identifier doi | 10.1115/1.2818093 | |
| journal fristpage | 97 | |
| journal lastpage | 104 | |
| identifier eissn | 0742-4795 | |
| keywords | Alloys | |
| keywords | Airfoils | |
| keywords | Crystals | |
| keywords | Coating processes | |
| keywords | Coatings | |
| keywords | Stability | |
| keywords | Temperature | |
| keywords | Engines | |
| keywords | Brazing | |
| keywords | Manufacturing technology | |
| keywords | Databases AND High temperature | |
| tree | Journal of Engineering for Gas Turbines and Power:;1998:;volume( 120 ):;issue: 001 | |
| contenttype | Fulltext |