Structure and composition of the surface layer of gas turbine blades
Conclusions The surface layer of a turbine blade consists of a succession of layers: recrystallized + fine-grained; and work hardened characterized by an increased hardness and lattice spacing of the solid solution; and an undeformed one. The content of alloy elements in the surface layer differs co...
Ausführliche Beschreibung
Gespeichert in:
| Autor*in: |
Kolomytsev, P. T. [verfasserIn] |
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| Format: |
Artikel |
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| Sprache: |
Englisch |
| Erschienen: |
1960 |
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| Schlagwörter: |
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| Anmerkung: |
© Consultants Bureau 1960 |
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| Übergeordnetes Werk: |
Enthalten in: Metal science and heat treatment - Kluwer Academic Publishers-Plenum Publishers, 1959, 2(1960), 9 vom: Sept., Seite 473-476 |
|---|---|
| Übergeordnetes Werk: |
volume:2 ; year:1960 ; number:9 ; month:09 ; pages:473-476 |
| Links: |
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| DOI / URN: |
10.1007/BF00649722 |
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OLC2047966043 |
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| 520 | |a Conclusions The surface layer of a turbine blade consists of a succession of layers: recrystallized + fine-grained; and work hardened characterized by an increased hardness and lattice spacing of the solid solution; and an undeformed one. The content of alloy elements in the surface layer differs considerably from the mean composition of the alloy.The adverse effect of surface work-hardening on heat resistance is associated with the large gradient of lattice parameters at high temperature and with consequent internal stresses.Cracking during extended operation at high temperature is caused by a depletion of the surface layer in alloy elements which, under normal conditions, ensure the high heat resistance of the alloy. | ||
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| 700 | 1 | |a Snetkov, A. Ya. |4 aut | |
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10.1007/BF00649722 doi (DE-627)OLC2047966043 (DE-He213)BF00649722-p DE-627 ger DE-627 rakwb eng 670 620 660 VZ Kolomytsev, P. T. verfasserin aut Structure and composition of the surface layer of gas turbine blades 1960 Text txt rdacontent ohne Hilfsmittel zu benutzen n rdamedia Band nc rdacarrier © Consultants Bureau 1960 Conclusions The surface layer of a turbine blade consists of a succession of layers: recrystallized + fine-grained; and work hardened characterized by an increased hardness and lattice spacing of the solid solution; and an undeformed one. The content of alloy elements in the surface layer differs considerably from the mean composition of the alloy.The adverse effect of surface work-hardening on heat resistance is associated with the large gradient of lattice parameters at high temperature and with consequent internal stresses.Cracking during extended operation at high temperature is caused by a depletion of the surface layer in alloy elements which, under normal conditions, ensure the high heat resistance of the alloy. Adverse Effect Solid Solution Surface Layer Normal Condition Internal Stress Samgin, A. A. aut Snetkov, A. Ya. aut Enthalten in Metal science and heat treatment Kluwer Academic Publishers-Plenum Publishers, 1959 2(1960), 9 vom: Sept., Seite 473-476 (DE-627)129596981 (DE-600)240858-2 (DE-576)015090159 0026-0673 nnns volume:2 year:1960 number:9 month:09 pages:473-476 https://doi.org/10.1007/BF00649722 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_OLC SSG-OLC-TEC GBV_ILN_30 GBV_ILN_70 GBV_ILN_2015 GBV_ILN_4046 GBV_ILN_4082 AR 2 1960 9 09 473-476 |
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10.1007/BF00649722 doi (DE-627)OLC2047966043 (DE-He213)BF00649722-p DE-627 ger DE-627 rakwb eng 670 620 660 VZ Kolomytsev, P. T. verfasserin aut Structure and composition of the surface layer of gas turbine blades 1960 Text txt rdacontent ohne Hilfsmittel zu benutzen n rdamedia Band nc rdacarrier © Consultants Bureau 1960 Conclusions The surface layer of a turbine blade consists of a succession of layers: recrystallized + fine-grained; and work hardened characterized by an increased hardness and lattice spacing of the solid solution; and an undeformed one. The content of alloy elements in the surface layer differs considerably from the mean composition of the alloy.The adverse effect of surface work-hardening on heat resistance is associated with the large gradient of lattice parameters at high temperature and with consequent internal stresses.Cracking during extended operation at high temperature is caused by a depletion of the surface layer in alloy elements which, under normal conditions, ensure the high heat resistance of the alloy. Adverse Effect Solid Solution Surface Layer Normal Condition Internal Stress Samgin, A. A. aut Snetkov, A. Ya. aut Enthalten in Metal science and heat treatment Kluwer Academic Publishers-Plenum Publishers, 1959 2(1960), 9 vom: Sept., Seite 473-476 (DE-627)129596981 (DE-600)240858-2 (DE-576)015090159 0026-0673 nnns volume:2 year:1960 number:9 month:09 pages:473-476 https://doi.org/10.1007/BF00649722 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_OLC SSG-OLC-TEC GBV_ILN_30 GBV_ILN_70 GBV_ILN_2015 GBV_ILN_4046 GBV_ILN_4082 AR 2 1960 9 09 473-476 |
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10.1007/BF00649722 doi (DE-627)OLC2047966043 (DE-He213)BF00649722-p DE-627 ger DE-627 rakwb eng 670 620 660 VZ Kolomytsev, P. T. verfasserin aut Structure and composition of the surface layer of gas turbine blades 1960 Text txt rdacontent ohne Hilfsmittel zu benutzen n rdamedia Band nc rdacarrier © Consultants Bureau 1960 Conclusions The surface layer of a turbine blade consists of a succession of layers: recrystallized + fine-grained; and work hardened characterized by an increased hardness and lattice spacing of the solid solution; and an undeformed one. The content of alloy elements in the surface layer differs considerably from the mean composition of the alloy.The adverse effect of surface work-hardening on heat resistance is associated with the large gradient of lattice parameters at high temperature and with consequent internal stresses.Cracking during extended operation at high temperature is caused by a depletion of the surface layer in alloy elements which, under normal conditions, ensure the high heat resistance of the alloy. Adverse Effect Solid Solution Surface Layer Normal Condition Internal Stress Samgin, A. A. aut Snetkov, A. Ya. aut Enthalten in Metal science and heat treatment Kluwer Academic Publishers-Plenum Publishers, 1959 2(1960), 9 vom: Sept., Seite 473-476 (DE-627)129596981 (DE-600)240858-2 (DE-576)015090159 0026-0673 nnns volume:2 year:1960 number:9 month:09 pages:473-476 https://doi.org/10.1007/BF00649722 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_OLC SSG-OLC-TEC GBV_ILN_30 GBV_ILN_70 GBV_ILN_2015 GBV_ILN_4046 GBV_ILN_4082 AR 2 1960 9 09 473-476 |
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10.1007/BF00649722 doi (DE-627)OLC2047966043 (DE-He213)BF00649722-p DE-627 ger DE-627 rakwb eng 670 620 660 VZ Kolomytsev, P. T. verfasserin aut Structure and composition of the surface layer of gas turbine blades 1960 Text txt rdacontent ohne Hilfsmittel zu benutzen n rdamedia Band nc rdacarrier © Consultants Bureau 1960 Conclusions The surface layer of a turbine blade consists of a succession of layers: recrystallized + fine-grained; and work hardened characterized by an increased hardness and lattice spacing of the solid solution; and an undeformed one. The content of alloy elements in the surface layer differs considerably from the mean composition of the alloy.The adverse effect of surface work-hardening on heat resistance is associated with the large gradient of lattice parameters at high temperature and with consequent internal stresses.Cracking during extended operation at high temperature is caused by a depletion of the surface layer in alloy elements which, under normal conditions, ensure the high heat resistance of the alloy. Adverse Effect Solid Solution Surface Layer Normal Condition Internal Stress Samgin, A. A. aut Snetkov, A. Ya. aut Enthalten in Metal science and heat treatment Kluwer Academic Publishers-Plenum Publishers, 1959 2(1960), 9 vom: Sept., Seite 473-476 (DE-627)129596981 (DE-600)240858-2 (DE-576)015090159 0026-0673 nnns volume:2 year:1960 number:9 month:09 pages:473-476 https://doi.org/10.1007/BF00649722 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_OLC SSG-OLC-TEC GBV_ILN_30 GBV_ILN_70 GBV_ILN_2015 GBV_ILN_4046 GBV_ILN_4082 AR 2 1960 9 09 473-476 |
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10.1007/BF00649722 doi (DE-627)OLC2047966043 (DE-He213)BF00649722-p DE-627 ger DE-627 rakwb eng 670 620 660 VZ Kolomytsev, P. T. verfasserin aut Structure and composition of the surface layer of gas turbine blades 1960 Text txt rdacontent ohne Hilfsmittel zu benutzen n rdamedia Band nc rdacarrier © Consultants Bureau 1960 Conclusions The surface layer of a turbine blade consists of a succession of layers: recrystallized + fine-grained; and work hardened characterized by an increased hardness and lattice spacing of the solid solution; and an undeformed one. The content of alloy elements in the surface layer differs considerably from the mean composition of the alloy.The adverse effect of surface work-hardening on heat resistance is associated with the large gradient of lattice parameters at high temperature and with consequent internal stresses.Cracking during extended operation at high temperature is caused by a depletion of the surface layer in alloy elements which, under normal conditions, ensure the high heat resistance of the alloy. Adverse Effect Solid Solution Surface Layer Normal Condition Internal Stress Samgin, A. A. aut Snetkov, A. Ya. aut Enthalten in Metal science and heat treatment Kluwer Academic Publishers-Plenum Publishers, 1959 2(1960), 9 vom: Sept., Seite 473-476 (DE-627)129596981 (DE-600)240858-2 (DE-576)015090159 0026-0673 nnns volume:2 year:1960 number:9 month:09 pages:473-476 https://doi.org/10.1007/BF00649722 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_OLC SSG-OLC-TEC GBV_ILN_30 GBV_ILN_70 GBV_ILN_2015 GBV_ILN_4046 GBV_ILN_4082 AR 2 1960 9 09 473-476 |
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Conclusions The surface layer of a turbine blade consists of a succession of layers: recrystallized + fine-grained; and work hardened characterized by an increased hardness and lattice spacing of the solid solution; and an undeformed one. The content of alloy elements in the surface layer differs considerably from the mean composition of the alloy.The adverse effect of surface work-hardening on heat resistance is associated with the large gradient of lattice parameters at high temperature and with consequent internal stresses.Cracking during extended operation at high temperature is caused by a depletion of the surface layer in alloy elements which, under normal conditions, ensure the high heat resistance of the alloy. © Consultants Bureau 1960 |
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Conclusions The surface layer of a turbine blade consists of a succession of layers: recrystallized + fine-grained; and work hardened characterized by an increased hardness and lattice spacing of the solid solution; and an undeformed one. The content of alloy elements in the surface layer differs considerably from the mean composition of the alloy.The adverse effect of surface work-hardening on heat resistance is associated with the large gradient of lattice parameters at high temperature and with consequent internal stresses.Cracking during extended operation at high temperature is caused by a depletion of the surface layer in alloy elements which, under normal conditions, ensure the high heat resistance of the alloy. © Consultants Bureau 1960 |
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Conclusions The surface layer of a turbine blade consists of a succession of layers: recrystallized + fine-grained; and work hardened characterized by an increased hardness and lattice spacing of the solid solution; and an undeformed one. The content of alloy elements in the surface layer differs considerably from the mean composition of the alloy.The adverse effect of surface work-hardening on heat resistance is associated with the large gradient of lattice parameters at high temperature and with consequent internal stresses.Cracking during extended operation at high temperature is caused by a depletion of the surface layer in alloy elements which, under normal conditions, ensure the high heat resistance of the alloy. © Consultants Bureau 1960 |
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T.</subfield><subfield code="e">verfasserin</subfield><subfield code="4">aut</subfield></datafield><datafield tag="245" ind1="1" ind2="0"><subfield code="a">Structure and composition of the surface layer of gas turbine blades</subfield></datafield><datafield tag="264" ind1=" " ind2="1"><subfield code="c">1960</subfield></datafield><datafield tag="336" ind1=" " ind2=" "><subfield code="a">Text</subfield><subfield code="b">txt</subfield><subfield code="2">rdacontent</subfield></datafield><datafield tag="337" ind1=" " ind2=" "><subfield code="a">ohne Hilfsmittel zu benutzen</subfield><subfield code="b">n</subfield><subfield code="2">rdamedia</subfield></datafield><datafield tag="338" ind1=" " ind2=" "><subfield code="a">Band</subfield><subfield code="b">nc</subfield><subfield code="2">rdacarrier</subfield></datafield><datafield tag="500" ind1=" " ind2=" "><subfield code="a">© Consultants Bureau 1960</subfield></datafield><datafield tag="520" ind1=" " ind2=" "><subfield code="a">Conclusions The surface layer of a turbine blade consists of a succession of layers: recrystallized + fine-grained; and work hardened characterized by an increased hardness and lattice spacing of the solid solution; and an undeformed one. The content of alloy elements in the surface layer differs considerably from the mean composition of the alloy.The adverse effect of surface work-hardening on heat resistance is associated with the large gradient of lattice parameters at high temperature and with consequent internal stresses.Cracking during extended operation at high temperature is caused by a depletion of the surface layer in alloy elements which, under normal conditions, ensure the high heat resistance of the alloy.</subfield></datafield><datafield tag="650" ind1=" " ind2="4"><subfield code="a">Adverse Effect</subfield></datafield><datafield tag="650" ind1=" " ind2="4"><subfield code="a">Solid Solution</subfield></datafield><datafield tag="650" ind1=" " ind2="4"><subfield code="a">Surface Layer</subfield></datafield><datafield tag="650" ind1=" " ind2="4"><subfield code="a">Normal Condition</subfield></datafield><datafield tag="650" ind1=" " ind2="4"><subfield code="a">Internal Stress</subfield></datafield><datafield tag="700" ind1="1" ind2=" "><subfield code="a">Samgin, A. A.</subfield><subfield code="4">aut</subfield></datafield><datafield tag="700" ind1="1" ind2=" "><subfield code="a">Snetkov, A. Ya.</subfield><subfield code="4">aut</subfield></datafield><datafield tag="773" ind1="0" ind2="8"><subfield code="i">Enthalten in</subfield><subfield code="t">Metal science and heat treatment</subfield><subfield code="d">Kluwer Academic Publishers-Plenum Publishers, 1959</subfield><subfield code="g">2(1960), 9 vom: Sept., Seite 473-476</subfield><subfield code="w">(DE-627)129596981</subfield><subfield code="w">(DE-600)240858-2</subfield><subfield code="w">(DE-576)015090159</subfield><subfield code="x">0026-0673</subfield><subfield code="7">nnns</subfield></datafield><datafield tag="773" ind1="1" ind2="8"><subfield code="g">volume:2</subfield><subfield code="g">year:1960</subfield><subfield code="g">number:9</subfield><subfield code="g">month:09</subfield><subfield code="g">pages:473-476</subfield></datafield><datafield tag="856" ind1="4" ind2="1"><subfield code="u">https://doi.org/10.1007/BF00649722</subfield><subfield code="z">lizenzpflichtig</subfield><subfield code="3">Volltext</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">GBV_USEFLAG_A</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">SYSFLAG_A</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">GBV_OLC</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">SSG-OLC-TEC</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">GBV_ILN_30</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">GBV_ILN_70</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">GBV_ILN_2015</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">GBV_ILN_4046</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">GBV_ILN_4082</subfield></datafield><datafield tag="951" ind1=" " ind2=" "><subfield code="a">AR</subfield></datafield><datafield tag="952" ind1=" " ind2=" "><subfield code="d">2</subfield><subfield code="j">1960</subfield><subfield code="e">9</subfield><subfield code="c">09</subfield><subfield code="h">473-476</subfield></datafield></record></collection>
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