Ni-Cr-Co alloy for advanced gas turbine engines

A gas turbine and engine technology, applied in the field of machinable high-strength alloys, can solve problems such as poor strain-aging cracking resistance

Inactive Publication Date: 2006-03-08
HAYNES INTERNATIONAL
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

This alloy has good thermal stability and creep strength, but the alloy is limited by poor resistance to strain age cracking
As these examples show, there are currently no alloys on the market that have a unique combination of three key properties: good creep strength and good thermal stability in the temperature range of 1600 to 1700°F and good resistance to strain age cracking

Method used

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  • Ni-Cr-Co alloy for advanced gas turbine engines
  • Ni-Cr-Co alloy for advanced gas turbine engines

Examples

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Embodiment Construction

[0013] The process-hardenable nickel-chromium-cobalt-based alloys described here possess sufficient creep strength, thermal stability, and resistance to strain age cracking to permit use in gas turbine transition tubes in sheet or thick plate form, and in Other product forms and for other severe gas turbine applications. The combination of these important properties is obtained by controlling several important elements each having a certain function. The presence of γ-prime forming elements such as aluminum, titanium, and niobium can contribute significantly to high creep rupture strength by forming the γ-prime phase during the age hardening process. However, the total amount of aluminum, titanium, and niobium must be carefully controlled in order to allow good strain age cracking resistance. The addition of molybdenum and possibly tungsten provides additional creep rupture strength through solid solution strengthening. In addition, however, the total concentration of molybd...

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Abstract

A wrought age-hardenable nickel-chromium-cobalt based alloy suitable for use in high temperature gas turbine transition ducts possessing a combination of three specific key properties, namely resistance to strain age cracking, good thermal stability, and good creep-rupture strength contains in weight percent 17 to 22 chromium, 8 to 15 cobalt, 4.0 to 9.5 molybdenum, up to 7 tungsten, 1.28 to 1.65 aluminum, 1.50 to 2.30 titanium, up to 0.80 niobium, 0.01 to 0.2 carbon, up to 0.01 boron, and up to 3 iron, with a balance of nickel and impurities. Certain alloying elements must be present in amounts according to two equations here disclosed.

Description

technical field [0001] The present invention relates to machinable high strength alloys for high temperature applications. In particular, the present invention relates to alloys having sufficient creep strength, thermal stability, and resistance to strain age cracking to permit fabrication and use in gas turbine transition ducts and other gas turbine components. Background technique [0002] To meet increasing operating efficiency requirements, gas turbine engine designers desire to use increasingly higher operating temperatures. However, the properties of the material often limit the ability to increase the operating temperature. One application with this limitation is a gas turbine transition duct. Transition pipes are usually welded elements made of sheet or thin plate material and therefore need to be weldable as well as machinable. Gamma-prime strengthened alloys are often used in transition tubes because of their high strength at elevated temperatures. However, cur...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C22C19/05C22C30/00B22D17/00B22F3/00
CPCC22C19/056C22C19/055C22C19/05
Inventor L·M·小派克
Owner HAYNES INTERNATIONAL
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