US2005152805A1PendingUtilityA1
Method for forming a wear-resistant hard-face contact area on a workpiece, such as a gas turbine engine part
Priority: Jan 8, 2004Filed: Jan 8, 2004Published: Jul 14, 2005
Est. expiryJan 8, 2024(expired)· nominal 20-yr term from priority
B23K 35/3046B22F 7/08C22C 19/056F01D 5/005C22F 1/10Y02T50/60F05D 2300/506C23C 10/28F05D 2230/31C23C 26/00F01D 5/288B22F 2998/10B22F 7/062C22C 19/07
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Claims
Abstract
A method for forming a wear-resistant hardfaced contact area on the shroud section of a gas turbine engine blade. A predetermined contact area of a shroud section of a gas turbine engine blade is selectively coated with a high-density hardface coating material. The hardface coating material is capable of forming a diffusion boundary between the hardface coating material and the shroud section. A hot isostatic heat treatment process is performed to form the diffusion boundary between the hardface coating material and the shroud section to form a wear-resistant hardfaced contact area diffusion bonded to the shroud section. Depending on the coating process, and the necessity for doing so, the predetermined contact area can be masked off before the step of selectively coating. A sintering heat treatment can be perfomed before the step of performing the hot isostatic heat treatment to limit the occurrence bubbles on the surface of the hardface coating material after the isostatic heat treatment step. The sintering heat treatment may be performed at a temperature substantially the same as the temperature of the hot isostatic heat treatment. The hardface coating material may comprise an alloy with substantially no oxide forming constituents so as to avoid the formation of oxide inclusions in the coating material.
Claims
exact text as granted — not AI-modified1 ). A method of forming a wear-resistant hardfaced contact area, comprising the steps of:
Selectively coating a predetermined contact area of a workpiece with a hardface coating material capable of forming a diffusion boundary between the hardface coating material and the workpiece; and Performing a hot isostatic heat treatment process to form the diffusion boundary between the hardface coating material and the workpiece to form a wear-resistant hardfaced contact area diffusion bonded to the workpiece.
2 ). A method of forming a wear-resistant hardfaced contact area according to claim 1; further comprising the step of masking off the predetermined contact area before the step of selectively coating.
3 ). A method of forming a wear-resistant hardfaced contact area according to claim 1; further comprising the step of performing a sintering heat treatment before the step of performing the hot isostatic heat treatment to limit the occurrence of bubbles on the surface of the hardface coating material after the isostatic heat treatment step.
4 ). A method of forming a wear-resistant hardfaced contact area according to claim 3; wherein the sintering heat treatment is performed at a temperature substantially the same as the temperature of the hot isostatic heat treatment.
5 ). A method of forming a wear-resistant hardfaced contact area according to claim 1; wherein the hardface coating material comprises an alloy with substantially no oxide forming constituents so as to avoid the formation of oxide inclusions in the coating material.
6 ). A method of forming a wear-resistant hardfaced contact area according to claim 1; wherein the hardface coating material comprise an alloy characterized by improved oxidation and wear resistance at elevated temperatures consisting essentially in weight percent of about:
Percent
Carbon
0.07-1.00
Manganese
1.00
Silicon
1.00
Chromium
26.00-30.00
Nickel
4.00-6.00
Tungsten
18.00-21.00
Boron
.005-0.100
Vanadium
0.75-1.25
Iron
3.00
Lanthanum
0.02-0.12
Cobalt
remainder
7 ). A method of forming a wear-resistant hardfaced contact area according to claim 1; wherein the hardface coating material comprise an alloy characterized by improved oxidation and wear resistance at elevated temperatures consisting essentially in weight percent of about:
Percent
Carbon
0.08 max
Silicon
3.00-3.80
Phosphorus
0.03 max
Sulfur
0.03 max
Chromium
16.50-18.50
Molybdenum
27.00-30.00
Nickel + Iron
3.00 max
Nitrogen
0.07 max
Oxygen
0.05 max
Lanthanum
0.02-0.12
Cobalt
remainder
8 ). A method of forming a wear-resistant hardfaced contact area on the shroud section of a gas turbine engine blade, comprising the steps of:
Selectively coating a predetermined contact area of a shroud section of a gas turbine engine blade with a hardface coating material capable of forming a diffusion boundary between the hardface coating material and the shroud section; and Performing a hot isostatic heat treatment process to form the diffusion boundary between the hardface coating material and the shroud section to form a wear-resistant hardfaced contact area diffusion bonded to the shroud section.
9 ). A method of forming a wear-resistant hardfaced contact area on the shroud section of a gas turbine engine blade according to claim 8; further comprising the step of masking off the predetermined contact area before the step of selectively coating.
10 ). method of forming a wear-resistant hardfaced contact area on the shroud section of a gas turbine engine blade according to claim 8; further comprising the step of performing a sintering heat treatment before the step of performing the hot isostatic heat treatment to limit the occurrence of bubbles on the surface of the hardface coating material after the isostatic heat treatment step.
11 ). A method of forming a wear-resistant hardfaced contact area on the shroud section of a gas turbine engine blade according to claim 10; wherein the sintering heat treatment is performed at a temperature substantially the same as the temperature of the hot isostatic heat treatment.
12 ). A method of forming a wear-resistant hardfaced contact area on the shroud section of a gas turbine engine blade according to claim 8; wherein the hardface coating material comprises an alloy with substantially no oxide forming constituents so as to avoid the formation of oxide inclusions in the coating material.
13 ). A method of forming a wear-resistant hardfaced contact area on the shroud section of a gas turbine engine blade according to claim 8; wherein the hardface coating material comprise an alloy characterized by improved oxidation and wear resistance at elevated temperatures consisting essentially in weight percent of about:
Percent
Carbon
0.07-1.00
Manganese
1.00
Silicon
1.00
Chromium
26.00-30.00
Nickel
4.00-6.00
Tungsten
18.00-21.00
Boron
.005-0.100
Vanadium
0.75-1.25
Iron
3.00
Lanthanum
0.02-0.12
Cobalt
remainder
14 ). A method of forming a wear-resistant hardfaced contact area on the shroud section of a gas turbine engine blade according to claim 8; wherein the hardface coating material comprise an alloy characterized by improved oxidation and wear resistance at elevated temperatures consisting essentially in weight percent of about:
Percent
Carbon
0.08 max
Silicon
3.00-3.80
Phosphorus
0.03 max
Sulfur
0.03 max
Chromium
16.50-18.50
Molybdenum
27.00-30.00
Nickel + Iron
3.00 max
Nitrogen
0.07 max
Oxygen
0.05 max
Lanthanum
0.02-0.12
Cobalt
remainderJoin the waitlist — get patent alerts
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