FATIGUE CRACK GROWTH BEHAVIOUR OF AA6013 ALUMINUM ALLOY: Fatigue of AA6013
5 Angebote vergleichen
| Preise | 2013 | 2014 | 2015 |
|---|---|---|---|
| Schnitt | € 47,02 | € 52,79 | € 61,08 |
| Nachfrage |
1
Symbolbild
Fatigue Crack Growth Behaviour of Aa6013 Aluminum Alloy
DE PB NWISBN: 9783639129762 bzw. 3639129768, in Deutsch, VDM Verlag, Taschenbuch, neu.
Von Händler/Antiquariat, BuySomeBooks [52360437], Las Vegas, NV, U.S.A.
Paperback. 104 pages. Dimensions: 8.7in. x 5.9in. x 0.2in.The effect of different aging treatments on fatigue crack growth behavior of AA6013 aluminum alloy was investigated. C(T) (Compact Tension) specimens were prepared in L-T and T-L direction for fatigue crack growth tests. Samples were in T651 as received, T42 which is solution heat treated at 538 C for 90 minutes, water quenched and aged in room temperature for 96 hours, and one group of samples were overaged at 245 C for 12 hours after T42 condition was achieved. Hardness and conductivity measurements were achieved for all conditions after the heat treatments. Fatigue crack growth tests were performed at as received condition T651, T42 and 245 C aged samples in laboratory air with sinusoidal loading of stress ratio R0. 1 and at a frequency of 1 Hz. The highest fatigue crack growth resistance is observed for T651 T-L and 245 C overaged L-T condition. This item ships from multiple locations. Your book may arrive from Roseburg,OR, La Vergne,TN.
Paperback. 104 pages. Dimensions: 8.7in. x 5.9in. x 0.2in.The effect of different aging treatments on fatigue crack growth behavior of AA6013 aluminum alloy was investigated. C(T) (Compact Tension) specimens were prepared in L-T and T-L direction for fatigue crack growth tests. Samples were in T651 as received, T42 which is solution heat treated at 538 C for 90 minutes, water quenched and aged in room temperature for 96 hours, and one group of samples were overaged at 245 C for 12 hours after T42 condition was achieved. Hardness and conductivity measurements were achieved for all conditions after the heat treatments. Fatigue crack growth tests were performed at as received condition T651, T42 and 245 C aged samples in laboratory air with sinusoidal loading of stress ratio R0. 1 and at a frequency of 1 Hz. The highest fatigue crack growth resistance is observed for T651 T-L and 245 C overaged L-T condition. This item ships from multiple locations. Your book may arrive from Roseburg,OR, La Vergne,TN.
2
FATIGUE CRACK GROWTH BEHAVIOUR OF AA6013 ALUMINUM ALLOY: Fatigue of AA6013
DE PB NWISBN: 9783639129762 bzw. 3639129768, in Deutsch, VDM Verlag Dr. Müller, Saarbrücken, Deutschland, Taschenbuch, neu.
Von Händler/Antiquariat, BuySomeBooks [52360437], Las Vegas, NV, U.S.A.
This item is printed on demand. Paperback. The effect of different aging treatments on fatigue crack growth behavior of AA6013 aluminum alloy was investigated. C(T) (Compact Tension) specimens were prepared in L-T and T-L direction for fatigue crack growth tests. Samples were in T651 as received, T42 which is solution heat treated at 538 C for 90 minutes, water quenched and aged in room temperature for 96 hours, and one group of samples were overaged at 245 C for 12 hours after T42 condition was achieved. Hardness and conductivity measurements were achieved for all conditions after the heat treatments. Fatigue crack growth tests were performed at as received condition T651, T42 and 245 C aged samples in laboratory air with sinusoidal loading of stress ratio R0. 1 and at a frequency of 1 Hz. The highest fatigue crack growth resistance is observed for T651 T-L and 245 C overaged L-T condition. This item ships from La Vergne,TN.
This item is printed on demand. Paperback. The effect of different aging treatments on fatigue crack growth behavior of AA6013 aluminum alloy was investigated. C(T) (Compact Tension) specimens were prepared in L-T and T-L direction for fatigue crack growth tests. Samples were in T651 as received, T42 which is solution heat treated at 538 C for 90 minutes, water quenched and aged in room temperature for 96 hours, and one group of samples were overaged at 245 C for 12 hours after T42 condition was achieved. Hardness and conductivity measurements were achieved for all conditions after the heat treatments. Fatigue crack growth tests were performed at as received condition T651, T42 and 245 C aged samples in laboratory air with sinusoidal loading of stress ratio R0. 1 and at a frequency of 1 Hz. The highest fatigue crack growth resistance is observed for T651 T-L and 245 C overaged L-T condition. This item ships from La Vergne,TN.
3
FATIGUE CRACK GROWTH BEHAVIOUR OF AA6013 ALUMINUMALLOY (2009)
DE PB NW RPISBN: 9783639129762 bzw. 3639129768, in Deutsch, Vdm Verlag Mrz 2009, Taschenbuch, neu, Nachdruck.
Von Händler/Antiquariat, AHA-BUCH GmbH [51283250], Einbeck, NDS, Germany.
This item is printed on demand - Print on Demand Titel. - The effect of different aging treatments on fatigue crack growth behavior of AA6013 aluminum alloy was investigated. C(T) (Compact Tension) specimens were prepared in L-T and T-L direction for fatigue crack growth tests. Samples were in T651 as received, T42 which is solution heat treated at 538 ºC for 90 minutes, water quenched and aged in room temperature for 96 hours, and one group of samples were overaged at 245 ºC for 12 hours after T42 condition was achieved. Hardness and conductivity measurements were achieved for all conditions after the heat treatments. Fatigue crack growth tests were performed at as received condition T651, T42 and 245 ºC aged samples in laboratory air with sinusoidal loading of stress ratio R=0.1 and at a frequency of 1 Hz. The highest fatigue crack growth resistance is observed for T651 T-L and 245 ºC overaged L-T condition. 104 pp. Englisch.
This item is printed on demand - Print on Demand Titel. - The effect of different aging treatments on fatigue crack growth behavior of AA6013 aluminum alloy was investigated. C(T) (Compact Tension) specimens were prepared in L-T and T-L direction for fatigue crack growth tests. Samples were in T651 as received, T42 which is solution heat treated at 538 ºC for 90 minutes, water quenched and aged in room temperature for 96 hours, and one group of samples were overaged at 245 ºC for 12 hours after T42 condition was achieved. Hardness and conductivity measurements were achieved for all conditions after the heat treatments. Fatigue crack growth tests were performed at as received condition T651, T42 and 245 ºC aged samples in laboratory air with sinusoidal loading of stress ratio R=0.1 and at a frequency of 1 Hz. The highest fatigue crack growth resistance is observed for T651 T-L and 245 ºC overaged L-T condition. 104 pp. Englisch.
4
Symbolbild
FATIGUE CRACK GROWTH BEHAVIOUR OF AA6013 ALUMINUMALLOY (2009)
DE PB NW RPISBN: 9783639129762 bzw. 3639129768, in Deutsch, VDM Verlag Mrz 2009, Taschenbuch, neu, Nachdruck.
Von Händler/Antiquariat, AHA-BUCH GmbH [51283250], Einbeck, Germany.
This item is printed on demand - Print on Demand Titel. Neuware - The effect of different aging treatments on fatigue crack growth behavior of AA6013 aluminum alloy was investigated. C(T) (Compact Tension) specimens were prepared in L-T and T-L direction for fatigue crack growth tests. Samples were in T651 as received, T42 which is solution heat treated at 538 ºC for 90 minutes, water quenched and aged in room temperature for 96 hours, and one group of samples were overaged at 245 ºC for 12 hours after T42 condition was achieved. Hardness and conductivity measurements were achieved for all conditions after the heat treatments. Fatigue crack growth tests were performed at as received condition T651, T42 and 245 ºC aged samples in laboratory air with sinusoidal loading of stress ratio R=0.1 and at a frequency of 1 Hz. The highest fatigue crack growth resistance is observed for T651 T-L and 245 ºC overaged L-T condition. 104 pp. Englisch.
This item is printed on demand - Print on Demand Titel. Neuware - The effect of different aging treatments on fatigue crack growth behavior of AA6013 aluminum alloy was investigated. C(T) (Compact Tension) specimens were prepared in L-T and T-L direction for fatigue crack growth tests. Samples were in T651 as received, T42 which is solution heat treated at 538 ºC for 90 minutes, water quenched and aged in room temperature for 96 hours, and one group of samples were overaged at 245 ºC for 12 hours after T42 condition was achieved. Hardness and conductivity measurements were achieved for all conditions after the heat treatments. Fatigue crack growth tests were performed at as received condition T651, T42 and 245 ºC aged samples in laboratory air with sinusoidal loading of stress ratio R=0.1 and at a frequency of 1 Hz. The highest fatigue crack growth resistance is observed for T651 T-L and 245 ºC overaged L-T condition. 104 pp. Englisch.
Lade…