Martensitic alloy component and process of forming a martensitic alloy component

Patent metadata

Field	Value
Publication number	US-10760150-B2
Application number	US-201815933543-A
Country	US
Kind code	B2
Filing date	Mar 23, 2018
Priority date	Mar 23, 2018
Publication date	Sep 1, 2020
Grant date	Sep 1, 2020

Abstract

A martensitic alloy component includes by weight, 0.25% to 0.31% carbon (C), 2.1% to 3.0% manganese (Mn), 0.22% to 0.28% silicon (Si), 2.0% to 2.2% chromium (Cr), 0.45% to 0.55% molybdenum (Mo), 0.08% to 0.12% vanadium (V), and the balance is iron (Fe) and incidental impurities. The manganese-chromium martensitic alloy component has a hardenability corresponding to an ideal diameter of about 15 inches to about 30 inches or more.

First claim

The invention claimed is:

1. A martensitic alloy component, comprising by weight:
0.25% to 0.31% C;
2.1% to 3.0% Mn;
0.22% to 0.28% Si;
2.0% to 2.2% Cr;
0.45% to 0.55% Mo;
0.08% to 0.12% V; and

balance iron and incidental impurities; and
wherein the component is formed without Al, Ni, Ti, and Nb,
wherein the component is formed by austenitizing the alloy at a temperature of great than 870 degrees Celsius converting a thickest section of the alloy to an austenite, followed by quenching to eliminate a ferrite/pearlite or a bainite formation, and followed by tempering between 550 degrees Celsius and 650 degrees Celsius,
wherein the component has a fracture appearance transition temperature at a surface of the component of less than negative forty degrees Celsius and less than thirty degrees Celsius at a maximum thickness of the component, and
wherein the component has a hardenability corresponding to an ideal diameter of about 15 inches to about 30 inches or more.

2. The martensitic alloy component of claim 1 , wherein the component comprises 2.2% to 3.0% Mn.

3. The martensitic alloy component of claim 1 , wherein the component comprises 2.3% to 3.0% Mn.

4. The martensitic alloy component of claim 1 , wherein the component comprises 2.4% to 3.0% Mn.

5. The martensitic alloy component of claim 1 , wherein the component comprises 2.5% to 3.0% Mn.

6. The martensitic alloy component of claim 1 , wherein the component comprises 2.6% to 3.0% Mn.

7. The martensitic alloy component of claim 1 , wherein the component comprises 2.1% to 2.2% Cr.

8. The martensitic alloy component of claim 1 , wherein the component has a hardenability corresponding to an ideal diameter of from 20 inches to 30 inches.

9. The martensitic alloy component of claim 1 , wherein the component has a hardenability corresponding to an ideal diameter of about 30 inches.

10. The martensitic alloy component of claim 1 , wherein the component is a turbomachine rotor shaft.

11. The martensitic alloy component of claim 1 , wherein the component is a turbomachine part.

12. The martensitic alloy component of claim 1 , wherein the component is a wind turbine part.

13. A turbomachine shaft comprising a martensitic alloy, the martensitic alloy including by weight:
0.25% to 0.31% C;
2.1% to 3.0% Mn;
0.22% to 0.28% Si;
2.0% to 2.2% Cr;
0.45% to 0.55% Mo;
0.08% to 0.12% V;

balance iron and incidental impurities; and
wherein the component is formed without Al, Ni, Ti, and Nb,
wherein the component is formed by austenitizing the alloy at a temperature of great than 870 degrees Celsius converting a thickest section of the alloy to an austenite, followed by quenching to eliminate a ferrite/pearlite or a bainite formation, and followed by tempering between 550 degrees Celsius and 650 degrees Celsius,
wherein the component has a fracture appearance transition temperature at a surface of the component of less than negative forty degrees Celsius and less than thirty degrees Celsius at a maximum thickness of the component, and
wherein the martensitic alloy has a hardenability corresponding to an ideal diameter of about 20 inches to about 30 inches or more.

14. The turbomachine shaft of claim 13 , wherein the martensitic alloy includes 2.2% to 3.0% Mn.

15. The turbomachine shaft of claim 13 , wherein the martensitic alloy includes 2.3% to 3.0% Mn.

16. The turbomachine shaft of claim 13 , wherein the martensitic alloy includes 2.5% to 3.0% Mn.

17. The turbomachine shaft of claim 13 , wherein the martensitic alloy includes 2.6% to 3.0% Mn.

18. A process of forming a martensitic alloy component, the process comprising:
forging an alloy comprising by weight:
0.25% to 0.31% C;
2.1% to 3.0% Mn;
0.22% to 0.28% Si;
2.0% to 2.2% Cr;
0.45% to 0.55% Mo;
0.08% to 0.12% V;

balance iron and incidental impurities; and
wherein the component is formed without Al, Ni, Ti, and Nb,
wherein the component is formed by austenitizing the alloy at a temperature of great than 870 degrees Celsius converting a thickest section of the alloy to an austenite, followed by quenching to eliminate a ferrite/pearlite or a bainite formation, and followed by tempering between 550 degrees Celsius and 650 degrees Celsius,
wherein the component has a fracture appearance transition temperature at a surface of the component of less than negative forty degrees Celsius and less than thirty degrees Celsius at a maximum thickness of the component, and
wherein the component has a hardenability corresponding to an ideal diameter of 20 inches to 30 inches or more.

19. The process of claim 18 , wherein the component has a thickness of greater than 20 inches.

20. The process of claim 18 , wherein the component is turbomachine shaft or a wind turbine shaft.

Assignees

• Gen Electric

Inventors

• Majka Theodore Francis

Classifications

• C21D9/38 Primary

  for roll bodies · CPC title

• C22C38/04

  containing manganese · CPC title

• C22C38/22

  with molybdenum or tungsten · CPC title

• C22C38/24

  with vanadium · CPC title

• C22C38/02

  containing silicon · CPC title