公开(公告)号：JPH11315701A

公开(公告)日：1999-11-16

申请号：JP4823999

申请日：1999-02-25

Applicant: UNITED TECHNOLOGIES CORP

Inventor： HOLLIS TERRY L ,  RISING THOMAS J ,  DORRANCE JOHN G ,  BEEMAN JR BRUCE I

IPC: F01D5/28 ,  C22C9/01 ,  C23C4/00 ,  C23C4/08 ,  F01D5/30

Abstract: PROBLEM TO BE SOLVED: To prevent abrasion between laminated base plates by applying abrasion resistance coating made of a specified aluminum-bronze alloy, which is the same material as one used in the laminated titanium alloy base plates, between the laminated plates. SOLUTION: In a gas turbine engine, each rotor stage 10 has a plurality of moving blades 12 each of which is provided with a vane 22 and a blade root 24, and a rotor disc 14. The blade root 24 of each blade 12 is accommodated in one of blade installation slots 20 arranged in the disc 14. In order to minimize abrasion, a lubricating abrasion prevention coating 26 is formed either on the blade root 24 or one of the blade installation slots 20, such that, when the blade root is accommodated in the blade installation slot 20, the abrasion resistance coating 26 is disposed between the blade root 24 and the blade installation slot 20. The abrasion resistance coating 20 consists of aluminum bronze alloy powder composed of Al 9.0 to 11.0%, Fe 0.0 to 1.50%, and Cu for the rest.

公开(公告)号：DE69933797D1

公开(公告)日：2006-12-07

申请号：DE69933797

申请日：1999-02-26

Applicant: UNITED TECHNOLOGIES CORP

Inventor： HOLLIS TERRY L ,  RISING THOMAS J ,  DORRANCE JOHN G ,  BEEMAN BRUCE I JR

IPC: F01D5/28 ,  F01D5/30 ,  C22C9/01 ,  C23C4/00 ,  C23C4/08

Abstract: A rotor blade (12) for a gas turbine engine rotor stage (10) is provided and comprises an airfoil (22) with a blade root (24) attached thereto and an aluminium bronze alloy wear resistant coating consisting essentially of 9.0 - 11.0% aluminium (Al), 0.0 - 1.50% iron (Fe), and a remainder of copper (Cu).

公开(公告)号：DE69926558D1

公开(公告)日：2005-09-15

申请号：DE69926558

申请日：1999-02-26

Applicant: UNITED TECHNOLOGIES CORP

Inventor： HOLLIS TERRY L ,  DORRANCE JOHN G ,  RISING THOMAS J ,  BEEMAN BRUCE I

IPC: F01D5/28 ,  C22C9/01 ,  C23C4/00 ,  C23C4/08 ,  F01D5/30

Abstract: A rotor blade (12) for a gas turbine engine rotor stage (10) is provided and comprises an airfoil (22) with a blade root (24) attached thereto and an aluminium bronze alloy wear resistant coating consisting essentially of 9.0 - 11.0% aluminium (Al), 0.0 - 1.50% iron (Fe), and a remainder of copper (Cu).

公开(公告)号：DE69933797T2

公开(公告)日：2007-09-13

申请号：DE69933797

申请日：1999-02-26

Applicant: UNITED TECHNOLOGIES CORP

Inventor： HOLLIS TERRY L ,  RISING THOMAS J ,  DORRANCE JOHN G ,  BEEMAN BRUCE I JR

IPC: F01D5/28 ,  F01D5/30 ,  C22C9/01 ,  C23C4/00 ,  C23C4/08

Abstract: A rotor blade (12) for a gas turbine engine rotor stage (10) is provided and comprises an airfoil (22) with a blade root (24) attached thereto and an aluminium bronze alloy wear resistant coating consisting essentially of 9.0 - 11.0% aluminium (Al), 0.0 - 1.50% iron (Fe), and a remainder of copper (Cu).

公开(公告)号：DE69926558T2

公开(公告)日：2006-06-08

申请号：DE69926558

申请日：1999-02-26

Applicant: UNITED TECHNOLOGIES CORP

Inventor： HOLLIS TERRY L ,  DORRANCE JOHN G ,  RISING THOMAS J ,  BEEMAN BRUCE I

IPC: F01D5/28 ,  F01D5/30 ,  C22C9/01 ,  C23C4/00 ,  C23C4/08

Abstract: A rotor blade (12) for a gas turbine engine rotor stage (10) is provided and comprises an airfoil (22) with a blade root (24) attached thereto and an aluminium bronze alloy wear resistant coating consisting essentially of 9.0 - 11.0% aluminium (Al), 0.0 - 1.50% iron (Fe), and a remainder of copper (Cu).