公开(公告)号：MX168891B

公开(公告)日：1993-06-14

申请号：MX714687

申请日：1987-06-30

Applicant: UNITED TECHNOLOGIES CORP

Inventor： PINKOWISH ALEXANDER ALFONS ,  HENRICKS ROBERT JACOBI ,  MARCIN JOHN JOSEPH ,  WAHL JACQUELINE BURNS

IPC: C22F1/00 ,  C22F1/10 ,  C23F1/00 ,  C30B33/00 ,  F01D5/28 ,  F02C3/06

Abstract: A coated nickel base superalloy single crystal turbine airfoil, blade (1), which is subject to gas turbine engine operation, can crack during refurbishment by a stress corrosion mechanism when exposed to certain corrosive media. The rapid thermal cycling that occurs during typical gas turbine engine operation results in high, non-uniform stresses across the airfoil, producing large localized residual strains in the article at ambient temperatures. Exposure to a corrosive environment, such as during coating removal or agressive cleaning, can produce chordwise cracks in a large number of the airfoils exposed. Such cracking is avoided by subjecting the articles to a preliminary stress relieving heat treatment which reduces the residual strains to a level below which cracking will not occur, prior to exposure to the corrosive media.

公开(公告)号：AU594478B2

公开(公告)日：1990-03-08

申请号：AU7498987

申请日：1987-06-29

Applicant: UNITED TECHNOLOGIES CORP

Inventor： HENRICKS ROBERT JACOBI ,  MARCIN JOHN JOSEPH ,  WAHL JACQUELINE BURNS ,  PINKOWISH ALEXANDER ALFONS

IPC: C22F1/10 ,  C22F1/00 ,  C23F1/00 ,  C30B33/00 ,  F01D5/28 ,  F02C3/06 ,  C22F1/02

Abstract: A coated nickel base superalloy single crystal turbine airfoil, blade (1), which is subject to gas turbine engine operation, can crack during refurbishment by a stress corrosion mechanism when exposed to certain corrosive media. The rapid thermal cycling that occurs during typical gas turbine engine operation results in high, non-uniform stresses across the airfoil, producing large localized residual strains in the article at ambient temperatures. Exposure to a corrosive environment, such as during coating removal or agressive cleaning, can produce chordwise cracks in a large number of the airfoils exposed. Such cracking is avoided by subjecting the articles to a preliminary stress relieving heat treatment which reduces the residual strains to a level below which cracking will not occur, prior to exposure to the corrosive media.

公开(公告)号：DE3761024D1

公开(公告)日：1989-12-28

申请号：DE3761024

申请日：1987-06-25

Applicant: UNITED TECHNOLOGIES CORP

Inventor： HENRICKS ROBERT JACOBI ,  MARCIN JOHN JOSEPH ,  WAHL JACQUELINE BURNS ,  PINKOWISH ALEXANDER ALFONS

IPC: C22F1/10 ,  C22F1/00 ,  C23F1/00 ,  C30B33/00 ,  F01D5/28 ,  F02C3/06 ,  C30B29/52

Abstract: A coated nickel base superalloy single crystal turbine airfoil, blade (1), which is subject to gas turbine engine operation, can crack during refurbishment by a stress corrosion mechanism when exposed to certain corrosive media. The rapid thermal cycling that occurs during typical gas turbine engine operation results in high, non-uniform stresses across the airfoil, producing large localized residual strains in the article at ambient temperatures. Exposure to a corrosive environment, such as during coating removal or agressive cleaning, can produce chordwise cracks in a large number of the airfoils exposed. Such cracking is avoided by subjecting the articles to a preliminary stress relieving heat treatment which reduces the residual strains to a level below which cracking will not occur, prior to exposure to the corrosive media.

公开(公告)号：AU7498987A

公开(公告)日：1988-01-07

申请号：AU7498987

申请日：1987-06-29

Applicant: UNITED TECHNOLOGIES CORP

Inventor： HENRICKS ROBERT JACOBI ,  MARCIN JOHN JOSEPH ,  WAHL JACQUELINE BURNS ,  PINKOWISH ALEXANDER ALFONS

IPC: C22F1/10 ,  C22F1/00 ,  C23F1/00 ,  C30B33/00 ,  F01D5/28 ,  F02C3/06 ,  C22F1/02

Abstract: A coated nickel base superalloy single crystal turbine airfoil, blade (1), which is subject to gas turbine engine operation, can crack during refurbishment by a stress corrosion mechanism when exposed to certain corrosive media. The rapid thermal cycling that occurs during typical gas turbine engine operation results in high, non-uniform stresses across the airfoil, producing large localized residual strains in the article at ambient temperatures. Exposure to a corrosive environment, such as during coating removal or agressive cleaning, can produce chordwise cracks in a large number of the airfoils exposed. Such cracking is avoided by subjecting the articles to a preliminary stress relieving heat treatment which reduces the residual strains to a level below which cracking will not occur, prior to exposure to the corrosive media.