公开(公告)号：CA1090168A

公开(公告)日：1980-11-25

申请号：CA267438

申请日：1976-12-08

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MAGYAR STEPHEN T ,  HIRAKIS EMANUEL C ,  GELL MAURICE L ,  FELTEN EDWARD J

IPC: C22C19/07 ,  C22F1/10 ,  B22D7/00

Abstract: Cobalt base alloys for use at elevated temperatures are disclosed that possess excellent resistance to oxidation/corrosion at elevated temperatures in combination with mechanical properties which exceed those of similar alloys currently in use. The sesistance to oxidation/corrosion is afforded by a particular combination of aluminum and chromium which act to form 8 protective aluminum layer and a synergistic combination of hafuium ant yttrium which act to promote adherence of the alumina. Refractory metal additions are utilized to improve the mechanical properties. The alloys of the invention are suited for use in gas turbine engines as well as industrial applications such as furnaces and chemical process apparatus.

公开(公告)号：CA1074674A

公开(公告)日：1980-04-01

申请号：CA259896

申请日：1976-08-26

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CETEL ALAN D ,  DUNTHORNE HECTOR B ,  GELL MAURICE L ,  HENRICKS ROBERT J

IPC: C22C19/05 ,  C22F1/10

Abstract: MULTI-STEP HEAT TREATMENT FOR SUPERALLOYS This invention relates to a multi-step heat treatment method for increasing the elevated temperature mechanical properties of nickel base superalloys. The heat treatment method is particularly applicable to those conventional alloys which have a cast structure consisting essentially of a gamma matrix containing a gamma prime second phase precipitate and regions of low melting constituents. The effect of the process of the invention is to maximize the volume fraction of the fine gamma prime precipitate, by a solution treatment and reprecipitation, without causing significant incipient melting.

公开(公告)号：CA1098425A

公开(公告)日：1981-03-31

申请号：CA291053

申请日：1977-11-16

Applicant: UNITED TECHNOLOGIES CORP

Inventor： GELL MAURICE L ,  DUHL DAVID N

IPC: C30B29/52 ,  C22C1/02 ,  C22C19/05 ,  C22F1/00 ,  C22F1/10 ,  C30B11/00 ,  C30B21/02 ,  C22C19/00 ,  B01J17/06

Abstract: Nickel base superalloy single crystal articles formed from an alloy family and heat treated are described as is the process employed. The articles are substantially free from cobalt and the grain boundary strengtheners such as carbon, boron, and zirconium. The heat treatment process homogenizes the microstructure, and refines the gamma prime morphology. The superalloy has particular utility in the fabrication of airfoils (blades and vanes) for use in gas turbine engines.