CA1202202A - Articles and parts resistant to stress corrosion cracking in reactor environments - Google Patents
Articles and parts resistant to stress corrosion cracking in reactor environmentsInfo
- Publication number
- CA1202202A CA1202202A CA000399645A CA399645A CA1202202A CA 1202202 A CA1202202 A CA 1202202A CA 000399645 A CA000399645 A CA 000399645A CA 399645 A CA399645 A CA 399645A CA 1202202 A CA1202202 A CA 1202202A
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- Prior art keywords
- stress corrosion
- corrosion cracking
- zirconium
- articles
- alloy
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Classifications
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C19/00—Alloys based on nickel or cobalt
- C22C19/03—Alloys based on nickel or cobalt based on nickel
- C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
- C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
- C22C19/056—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 10% but less than 20%
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Heat Treatment Of Articles (AREA)
Abstract
ABSTRACT OF THE DISCLOSURE
Age-hardenable nickel chromium alloys, when aged to a strength level of at least about 100,000 pounds per square inch yield, are improved against stress corrosion cracking when the zirconium content thereof is at least about 0.05%
up to about 0.2%.
Age-hardenable nickel chromium alloys, when aged to a strength level of at least about 100,000 pounds per square inch yield, are improved against stress corrosion cracking when the zirconium content thereof is at least about 0.05%
up to about 0.2%.
Description
~z~
PC-~823 The invention is directed to the provision of articles and parts which are resistan~ ~o stress corrosion cracking in aqueous environments such as those encountered in light wateE reactors.
. It has been ound that certain relatively highly stressed parts employed in light water nuclear reactor environments are subject to stress corrosion cracking wherein the ~art failed catastrophical~y without apparent damage.
Thus, relatively highly stressed parts ~uch as springs, bolts; valve stems, etc, produced of age hardened nickel-base alloys such a~ theses ~isclosed in U.S. Patents No.
PC-~823 The invention is directed to the provision of articles and parts which are resistan~ ~o stress corrosion cracking in aqueous environments such as those encountered in light wateE reactors.
. It has been ound that certain relatively highly stressed parts employed in light water nuclear reactor environments are subject to stress corrosion cracking wherein the ~art failed catastrophical~y without apparent damage.
Thus, relatively highly stressed parts ~uch as springs, bolts; valve stems, etc, produced of age hardened nickel-base alloys such a~ theses ~isclosed in U.S. Patents No.
2,57~193 and No~ 2~570,1g4 having a tensile yield strength of 100,000 lbs/in2 or higher have been subject to failure attrihuted to stress ~orrosion cracking in deaerated water at pH 10 at temperatures up to 360~C.
The failures encountered in ~ervice were quite unexpected and dismayingO It was known that over-aging h~at treatments were beneficial in improving resistance to stress corro~ion ~ra~king of age hardenable alloys and it was postulated that compo~itional changes in the alloy used could also improve stress corxosion cracking but no leads were available which would indicate the direction in which ~o proceed or the ingredient in the alloy which should ~e controlled in order to improve resistance to stress corrosion craclcing of age~hardenable alloys heat treated to provide a room temperatu~e yi~ld strength (0~2% offset) oP at least about lQ0,0~0 psi. The problem was Purther complicated in that not only was it desirable to obtain the property of resistance to stress corroslon cracking ~ut in addition the capability of proYiding a yield strength of design interest ~' ~2~ 2~32 was still to be retainedO It was known rom testing of wedge opening l~ading (WOL) ~tress corrosion specimens made of an es~ent1ally non-~a~in~ nickel-base alloy containing 15.7~ chromium~ 8.1~ iron, 00014% carbon, 0.29~ aluminum, Q.007% titanium, 0~0005~ sulfuY, 0.15% silicon, 0~ copper 0.006% boronJ 0~008% pho~porous~ 0.006~ nitro~en, 0.21~
zirconIum, subjected ~o deaerated, deionized water at p~I lQ
and a temperature of 360C tha~ cracking was observed a~ 7 and 16 weeks i~ two specimens of material whi~h had been annealed (solution treated) one hour at 1120C and water quenched but that when the same annealed material was then heated ("L" treatment) for 7 hours at 608C and alr cooled that no cracking was observed in the full 36~week course of the test. The alloy in the ann~aled condition would typically have a yield strength ak room temperature below 40/000 psi, and it was con~idered that no valid compar;son could be drawn from such an alloy to an age-hardenable alloy heat treated to provide a yield ~rength at room temperature o 100,000 psi or mor~.
~UM ~ RY OF THE VENTION
I~ has been discovered that age-hardenable alloys, aged to provide a yield strength (0.2~ ofset~ of at least about 100,000 pounds per square inch) containing, by weight, 0.08~ max~ carbon~ 1% max mangane e~ 5%-9~ iron, 0~01%
max. sulfur, 005~ maxO silicon, 005% maxO copper, 14~-17 chromium~ 0~4~ to 1~ aluminum~ 2.25%~2.75% titanium, 0.7~-1.2~ columbium and the balance essentially nickel, have much greater resistance to stress corrosion cracking in testing at 360C in deaerated, deionized water containing less than 50 parts ~er billion of oxygen and saturated with
The failures encountered in ~ervice were quite unexpected and dismayingO It was known that over-aging h~at treatments were beneficial in improving resistance to stress corro~ion ~ra~king of age hardenable alloys and it was postulated that compo~itional changes in the alloy used could also improve stress corxosion cracking but no leads were available which would indicate the direction in which ~o proceed or the ingredient in the alloy which should ~e controlled in order to improve resistance to stress corrosion craclcing of age~hardenable alloys heat treated to provide a room temperatu~e yi~ld strength (0~2% offset) oP at least about lQ0,0~0 psi. The problem was Purther complicated in that not only was it desirable to obtain the property of resistance to stress corroslon cracking ~ut in addition the capability of proYiding a yield strength of design interest ~' ~2~ 2~32 was still to be retainedO It was known rom testing of wedge opening l~ading (WOL) ~tress corrosion specimens made of an es~ent1ally non-~a~in~ nickel-base alloy containing 15.7~ chromium~ 8.1~ iron, 00014% carbon, 0.29~ aluminum, Q.007% titanium, 0~0005~ sulfuY, 0.15% silicon, 0~ copper 0.006% boronJ 0~008% pho~porous~ 0.006~ nitro~en, 0.21~
zirconIum, subjected ~o deaerated, deionized water at p~I lQ
and a temperature of 360C tha~ cracking was observed a~ 7 and 16 weeks i~ two specimens of material whi~h had been annealed (solution treated) one hour at 1120C and water quenched but that when the same annealed material was then heated ("L" treatment) for 7 hours at 608C and alr cooled that no cracking was observed in the full 36~week course of the test. The alloy in the ann~aled condition would typically have a yield strength ak room temperature below 40/000 psi, and it was con~idered that no valid compar;son could be drawn from such an alloy to an age-hardenable alloy heat treated to provide a yield ~rength at room temperature o 100,000 psi or mor~.
~UM ~ RY OF THE VENTION
I~ has been discovered that age-hardenable alloys, aged to provide a yield strength (0.2~ ofset~ of at least about 100,000 pounds per square inch) containing, by weight, 0.08~ max~ carbon~ 1% max mangane e~ 5%-9~ iron, 0~01%
max. sulfur, 005~ maxO silicon, 005% maxO copper, 14~-17 chromium~ 0~4~ to 1~ aluminum~ 2.25%~2.75% titanium, 0.7~-1.2~ columbium and the balance essentially nickel, have much greater resistance to stress corrosion cracking in testing at 360C in deaerated, deionized water containing less than 50 parts ~er billion of oxygen and saturated with
-3 PC-~823 hydrogen, when the zirconium content of the alloy is at least 0.07% and up to 0.15% or 0.2%.
DETAILED DESCRIPTION OF THE INVENTION
The invention is based on the discovery that age hardened nickel-base alloys having a yield strength oE at least about 100,000 lbs/in2 are much better protected against stress corrosion cracking by including in the alloy at ]east about 0.07% of zirconium.
This discovery i9 illustrated in the following examples.
LX~MPLE 1 Sixteen laboratory size heats of an alloy containing nom:inally 15% chromium, 7.5% iron, 1% columbium, 0.75% aluminum3 and 2.7% titanium with a balance essentia]ly nickel were produced and reduced to 0.5"
thick by 5" wide hot rolled plate. Certain of the alloys contained about O.U8~ zirconium while the others were essentially zirconium-free.
Half ~nch thick WOL specimens were prepared from each heat. The WOL
samp]es were fatlgue pre-cracked at room tempera~ure and bolt loaded to various starting stress intensities determined by a crack opening displacement gage inserted at the outer edge. Two or three WOI, samples were tested from each heat. Prior to machining, specimen blanks oF the WOL samples were subjected to a heat treatment comprising a solution at 1093C for 2 hours followed hy water quenching and an aging at 704C for 20 hours. The WOL samples were tested in deaerated pH 10 water at 360C. The samples were removed from test at Eour-week intervals and the crack lengths ~;;
'i .1 measured on the sîdes of the samples. These tests and earlier studies showe~ tha~ visihle crack propaga~ion halted after approximately six weeks of testing~ The total test time was 1~ weeksO Compositions of the heats are given on Table I and the results of the WOL test are given in Table XI.
The stress corrosion cracking resistance is measured in terms o the ~tress intensity at which s~ress corrosion crack propagation stopped, as measured on the frackure surfaces of samples that were mechanically broken open at room temper~ture after the stress corrosion test was comple ted~ The higher the KI~C~ value the greater is the resist-ance to stress corrosion cracking. The yield strength val.ues were determin~d by tensile tests at room temperature.
The results of Table II demonstrate that sta~isi-cally the alloys containing 0.08~ zirconium were signi~icantly higher in KISC~ value than were the low zirconium heats.
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T~I.E 2 5~RE:SS CORROSIO~ l~EST RESULTS
~ .
Yield Strength HeatZr KXSCC ~ksi in3 680F Water (ksi) 31. 9, 34 . 5 112 2 L 42 ., 4 ~ 45 .1 . 110 3 L 39 .1, 45 O 0, 41. ~ 116
DETAILED DESCRIPTION OF THE INVENTION
The invention is based on the discovery that age hardened nickel-base alloys having a yield strength oE at least about 100,000 lbs/in2 are much better protected against stress corrosion cracking by including in the alloy at ]east about 0.07% of zirconium.
This discovery i9 illustrated in the following examples.
LX~MPLE 1 Sixteen laboratory size heats of an alloy containing nom:inally 15% chromium, 7.5% iron, 1% columbium, 0.75% aluminum3 and 2.7% titanium with a balance essentia]ly nickel were produced and reduced to 0.5"
thick by 5" wide hot rolled plate. Certain of the alloys contained about O.U8~ zirconium while the others were essentially zirconium-free.
Half ~nch thick WOL specimens were prepared from each heat. The WOL
samp]es were fatlgue pre-cracked at room tempera~ure and bolt loaded to various starting stress intensities determined by a crack opening displacement gage inserted at the outer edge. Two or three WOI, samples were tested from each heat. Prior to machining, specimen blanks oF the WOL samples were subjected to a heat treatment comprising a solution at 1093C for 2 hours followed hy water quenching and an aging at 704C for 20 hours. The WOL samples were tested in deaerated pH 10 water at 360C. The samples were removed from test at Eour-week intervals and the crack lengths ~;;
'i .1 measured on the sîdes of the samples. These tests and earlier studies showe~ tha~ visihle crack propaga~ion halted after approximately six weeks of testing~ The total test time was 1~ weeksO Compositions of the heats are given on Table I and the results of the WOL test are given in Table XI.
The stress corrosion cracking resistance is measured in terms o the ~tress intensity at which s~ress corrosion crack propagation stopped, as measured on the frackure surfaces of samples that were mechanically broken open at room temper~ture after the stress corrosion test was comple ted~ The higher the KI~C~ value the greater is the resist-ance to stress corrosion cracking. The yield strength val.ues were determin~d by tensile tests at room temperature.
The results of Table II demonstrate that sta~isi-cally the alloys containing 0.08~ zirconium were signi~icantly higher in KISC~ value than were the low zirconium heats.
2~
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T~I.E 2 5~RE:SS CORROSIO~ l~EST RESULTS
~ .
Yield Strength HeatZr KXSCC ~ksi in3 680F Water (ksi) 31. 9, 34 . 5 112 2 L 42 ., 4 ~ 45 .1 . 110 3 L 39 .1, 45 O 0, 41. ~ 116
4 L 52 . 0, 51. 3 lQ8 ~ 5~ 9.1, 60.1 112 6 ~ ~ 55 7 49 . 3 107 7, E~ 55 ~ 56 . 1 115 8 E~ 57, S~.5 112 9 L 52 l 53 11 10. L 47 J 52 0 6, d~8 0 8 112 11 L . 53 " 55 . 9 112 12 L 54 .1~ 52 . 5 112 13 H 53, 56 . 7 l.l4 14 H 52 . 5, 61. 8 ~ 54 110 15 ~I 53 . ~, 61 . 1 ~ 52 , 115 16 H 54 ~ 5 ~ 5U .1 114 L = Low ~r O . 0059~'br H ~ High ~ O . 08%Zr XAMPL~ II
~ even heats having composi~ions set forth in Table III were pxoducedO
Tensile specimens and WOL tes~ specimens were prepared fro~ each oE these seven al~oys. All samples were solution trea~ed at 1093C or ~wo hours and water quenched and were then given an aging treatment at either 704C for 20 hours followed by air cocling ~treatment ~ or at 760C
for ~6 hours followed by air cooling (treatment B~. The results of the tensile and WOL testing are given in Table IVo The test conditions for WOL test were the same as those set forth in Example I hereinbefore.
Again the signiicance of increasing the zirconium content of the alloy is c~early set forth in comparing the RIScc values given in Table IV~
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~AiBLE 4 Heat ~ield Stren~th KIS(:C
Treatment tksi) 17 A 111 50.3, 39O7p 33 18 A 110 49 . 3, 47 ~19 ~ ~10 56.2p Ds7.8 , A 115 ~ 6 2 . 4 B 102 >61. 6 9 >50.9, 61~5 22 A 126 23~4, 34.. 6 23 ~ 1~4 ~ O 2, 4~ . 1 A = 1093C/2 hr. WQ ~ 704C~20 hr~ AC
B = 1093~C,/2 hr. WQ ~ 760C/~6 hr. AC
. g _ EX~MPLE III
Plate stock of co~mercial origin of an alloy having the ~omposition ~et forth .in Table V was obtained.
Tensile specimens and WOL test specimens of the type described hereinbefore in the Example I were prepared rom the alloy material~ -The results of the tensile tests on ~he heat treatedalloy specimens together With the KIScc results obtained for the various heat treatments are set forth in Table VT.
The heat treatment accorded each specimen is also included in Table VIo The data of Table VI demonstrate that the heat treatments produced underaged~ peaked aged and overage micro-structuresu The data of Table VI indicate however that neither underaging nor overaging produces a distinctively better combination of strength and cracking resistance.
Only the specimens aged for 96 hours at 760C appear tg possess distinctly better properties. The results of the heat treatment experiments indicate that the flexibility accorded through the heat treatment route is far less than that provided by changes in ailoy compositionD Wh.ile it is true that a substantial improYement in propert.ies was pro-duced by a 9~ hvur asing treatment, such a treatment is not considered to be ccmmercially practical~
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T~ 6 PRC)PERrrIES OF ALLOY 24 AS A
FUNC'rION OF HEAT TREATMENT
(All samples originally annealed for 2 hours at 1093nC and wat2r ~uenched) Yield P~ging H[eat Btrength KISCC
Treatment ~1) (ksi~ (ksi ~.
.~ . _ .. .. _ 593C/2û h 74 53, '18 649 C/20 h 99 ` ~12 ~ 41 704nc/20 h 105 42, 48 760C,/20 h 95 44 ;r 47 816~C/20 h 77 36 ~ 50 7~0~C/96 ~ ~0 58, ~1 Although the present invention has been described in conjunction wi~h preferred em~odi~nts, it is to be ~nde~-stood ~ha~ modi~ications and variations may be resorted to without departing from the spirit and scope of the inven tion, as those skilled in ~he art will readily unders~and.
Such modifications and variations are considered to be within the purview and scope of the inven~ion and appended claims.
~ ~3 -
~ even heats having composi~ions set forth in Table III were pxoducedO
Tensile specimens and WOL tes~ specimens were prepared fro~ each oE these seven al~oys. All samples were solution trea~ed at 1093C or ~wo hours and water quenched and were then given an aging treatment at either 704C for 20 hours followed by air cocling ~treatment ~ or at 760C
for ~6 hours followed by air cooling (treatment B~. The results of the tensile and WOL testing are given in Table IVo The test conditions for WOL test were the same as those set forth in Example I hereinbefore.
Again the signiicance of increasing the zirconium content of the alloy is c~early set forth in comparing the RIScc values given in Table IV~
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~AiBLE 4 Heat ~ield Stren~th KIS(:C
Treatment tksi) 17 A 111 50.3, 39O7p 33 18 A 110 49 . 3, 47 ~19 ~ ~10 56.2p Ds7.8 , A 115 ~ 6 2 . 4 B 102 >61. 6 9 >50.9, 61~5 22 A 126 23~4, 34.. 6 23 ~ 1~4 ~ O 2, 4~ . 1 A = 1093C/2 hr. WQ ~ 704C~20 hr~ AC
B = 1093~C,/2 hr. WQ ~ 760C/~6 hr. AC
. g _ EX~MPLE III
Plate stock of co~mercial origin of an alloy having the ~omposition ~et forth .in Table V was obtained.
Tensile specimens and WOL test specimens of the type described hereinbefore in the Example I were prepared rom the alloy material~ -The results of the tensile tests on ~he heat treatedalloy specimens together With the KIScc results obtained for the various heat treatments are set forth in Table VT.
The heat treatment accorded each specimen is also included in Table VIo The data of Table VI demonstrate that the heat treatments produced underaged~ peaked aged and overage micro-structuresu The data of Table VI indicate however that neither underaging nor overaging produces a distinctively better combination of strength and cracking resistance.
Only the specimens aged for 96 hours at 760C appear tg possess distinctly better properties. The results of the heat treatment experiments indicate that the flexibility accorded through the heat treatment route is far less than that provided by changes in ailoy compositionD Wh.ile it is true that a substantial improYement in propert.ies was pro-duced by a 9~ hvur asing treatment, such a treatment is not considered to be ccmmercially practical~
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T~ 6 PRC)PERrrIES OF ALLOY 24 AS A
FUNC'rION OF HEAT TREATMENT
(All samples originally annealed for 2 hours at 1093nC and wat2r ~uenched) Yield P~ging H[eat Btrength KISCC
Treatment ~1) (ksi~ (ksi ~.
.~ . _ .. .. _ 593C/2û h 74 53, '18 649 C/20 h 99 ` ~12 ~ 41 704nc/20 h 105 42, 48 760C,/20 h 95 44 ;r 47 816~C/20 h 77 36 ~ 50 7~0~C/96 ~ ~0 58, ~1 Although the present invention has been described in conjunction wi~h preferred em~odi~nts, it is to be ~nde~-stood ~ha~ modi~ications and variations may be resorted to without departing from the spirit and scope of the inven tion, as those skilled in ~he art will readily unders~and.
Such modifications and variations are considered to be within the purview and scope of the inven~ion and appended claims.
~ ~3 -
Claims (4)
1. An article subjected in use to conditions which promote failure by a stress corrosion cracking mechanism in a deaerated, aqueous environment inclusive of hydrogen made of an age hardened alloy containing about 0.07% to about 0.2% zirconium, up to 0.08% carbon, up to 1% manganese, up to 0.5% silicon, up to 0.5% copper, no more than 0.01% sulfur, about 5% to about 9% iron, about 14% to about 17%
chromium, about 0.4% to about 1% aluminum, about 2.25% to about 2.75%
titanium, about 0.7% to about 1.2% columbium, and the balance essentially nickel.
chromium, about 0.4% to about 1% aluminum, about 2.25% to about 2.75%
titanium, about 0.7% to about 1.2% columbium, and the balance essentially nickel.
2. An article according to claim 1 containing at least about 0.07%
and up to about 0.15% zirconium.
and up to about 0.15% zirconium.
3. An article according to claim 1 comprising a bolt.
4. An article according to claim 1 comprising a spring.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US26600581A | 1981-05-21 | 1981-05-21 | |
| US266,005 | 1981-05-21 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA1202202A true CA1202202A (en) | 1986-03-25 |
Family
ID=23012772
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA000399645A Expired CA1202202A (en) | 1981-05-21 | 1982-03-29 | Articles and parts resistant to stress corrosion cracking in reactor environments |
Country Status (3)
| Country | Link |
|---|---|
| EP (1) | EP0069452A1 (en) |
| JP (1) | JPS57198236A (en) |
| CA (1) | CA1202202A (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS63198316A (en) * | 1987-01-08 | 1988-08-17 | インコ、アロイス、インターナショナルインコーポレーテッド | Tray for processing silicon wafer |
| RU2089642C1 (en) * | 1995-11-14 | 1997-09-10 | Государственный научный центр РФ "Всероссийский научно-исследовательский институт неорганических материалов им.А.А.Бочвара" | Nickel-based alloy and its modification |
| CN110643857A (en) * | 2019-09-29 | 2020-01-03 | 西安欧中材料科技有限公司 | Nickel-based alloy powder without original grain boundary and preparation method thereof |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2570194A (en) * | 1946-04-09 | 1951-10-09 | Int Nickel Co | Production of high-temperature alloys and articles |
| US2570193A (en) * | 1946-04-09 | 1951-10-09 | Int Nickel Co | High-temperature alloys and articles |
| AT231737B (en) * | 1960-12-02 | 1964-02-10 | Birmingham Small Arms Co Ltd | Durable sintered alloy and process for its production |
-
1982
- 1982-03-29 CA CA000399645A patent/CA1202202A/en not_active Expired
- 1982-05-20 JP JP57085629A patent/JPS57198236A/en active Pending
- 1982-05-21 EP EP82302600A patent/EP0069452A1/en not_active Ceased
Also Published As
| Publication number | Publication date |
|---|---|
| EP0069452A1 (en) | 1983-01-12 |
| JPS57198236A (en) | 1982-12-04 |
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