公开(公告)号：GB2226050B

公开(公告)日：1993-04-07

申请号：GB8927672

申请日：1989-12-07

Applicant: UNITED TECHNOLOGIES CORP

Inventor： VINE RAYMOND W ,  ROBINS DONALD A ,  NORDSTROM DONALD G ,  GOODSTEIN MARK B

IPC: C23C4/02 ,  F01D11/12

Abstract: An abradable coating is described for interaction with a abrasive gas turbine engine component to provide sealing. The abradable coating comprises yttria stabilized zirconia with intentional porosity which is applied by plasma spraying to a MCrAlY bond coat which in turn rest on a superalloy substrate. The coating system is applied by plasma spraying. The coating system is adapted to interact with an abrasive coated abrasive treated gas turbine engine component.

公开(公告)号：FR2640688A1

公开(公告)日：1990-06-22

申请号：FR8916494

申请日：1989-12-13

Applicant: UNITED TECHNOLOGIES CORP

Inventor： VINE RAYMOND W ,  ROBBINS DONALD A ,  NORDSTROM DONALD G ,  GOODSTEIN MARK B

IPC: C23C4/02 ,  F01D11/12

Abstract: An abradable coating is described for interaction with a abrasive gas turbine engine component to provide sealing. The abradable coating comprises yttria stabilized zirconia with intentional porosity which is applied by plasma spraying to a MCrAlY bond coat which in turn rest on a superalloy substrate. The coating system is applied by plasma spraying. The coating system is adapted to interact with an abrasive coated abrasive treated gas turbine engine component.

公开(公告)号：DE69606366T2

公开(公告)日：2000-08-24

申请号：DE69606366

申请日：1996-08-21

Applicant: UNITED TECHNOLOGIES CORP

Inventor： LIEBKE WILLIAM R ,  DAWSON DAVID R ,  FREDETTE MARK A ,  GOODSTEIN MARK B

IPC: B24B31/00 ,  B24B31/116 ,  F01D5/18

Abstract: A method of removing excess MCrAIY overlay coating from within a cooling hole of an aluminide coated gas turbine engine component is disclosed. The method includes providing a gas turbine engine component having an internal surface (4), an outer surface (6) and a root end (8). The component also includes at least one cooling hole (10) extending from the internal surface (4) to the outer surface (6), wherein the internal surface(4) of the component is coated with a corrosion resistant aluminide coating. An MCrAIY overlay coating (12) is also located on the outer surface (6) and inside a portion of the cooling hole (10). An abrasive slurry is forced into the gas turbine engine component from the outside of the component to the inside of the component, through the cooling hole (10), such that the slurry flows through the internal surface (4) of the component and removes at least a portion of the overlay coating (12) located inside the cooling hole (10) without adversely affecting the internal surface (4) of the component. The abrasive slurry subsequently exits the component through the root end (8).

公开(公告)号：GB2226050A

公开(公告)日：1990-06-20

申请号：GB8927672

申请日：1989-12-07

Applicant: UNITED TECHNOLOGIES CORP

Inventor： VINE RAYMOND W ,  ROBINS DONALD A ,  NORDSTROM DONALD G ,  GOODSTEIN MARK B

IPC: C23C4/02 ,  F01D11/12

Abstract: An abradable coating is described for interaction with a abrasive gas turbine engine component to provide sealing. The abradable coating comprises yttria stabilized zirconia with intentional porosity which is applied by plasma spraying to a MCrAlY bond coat which in turn rest on a superalloy substrate. The coating system is applied by plasma spraying. The coating system is adapted to interact with an abrasive coated abrasive treated gas turbine engine component.

公开(公告)号：DE69606366D1

公开(公告)日：2000-03-02

申请号：DE69606366

申请日：1996-08-21

Applicant: UNITED TECHNOLOGIES CORP

Inventor： LIEBKE WILLIAM R ,  DAWSON DAVID R ,  FREDETTE MARK A ,  GOODSTEIN MARK B

IPC: B24B31/00 ,  B24B31/116 ,  F01D5/18

Abstract: A method of removing excess MCrAIY overlay coating from within a cooling hole of an aluminide coated gas turbine engine component is disclosed. The method includes providing a gas turbine engine component having an internal surface (4), an outer surface (6) and a root end (8). The component also includes at least one cooling hole (10) extending from the internal surface (4) to the outer surface (6), wherein the internal surface(4) of the component is coated with a corrosion resistant aluminide coating. An MCrAIY overlay coating (12) is also located on the outer surface (6) and inside a portion of the cooling hole (10). An abrasive slurry is forced into the gas turbine engine component from the outside of the component to the inside of the component, through the cooling hole (10), such that the slurry flows through the internal surface (4) of the component and removes at least a portion of the overlay coating (12) located inside the cooling hole (10) without adversely affecting the internal surface (4) of the component. The abrasive slurry subsequently exits the component through the root end (8).

公开(公告)号：SG47171A1

公开(公告)日：1998-03-20

申请号：SG1996010504

申请日：1996-08-24

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DAWSON DAVID R ,  FREDETTE MARK A ,  GOODSTEIN MARK B ,  LIEBKE WILLIAM R

IPC: B24B31/00 ,  B24B31/116 ,  F01D5/18 ,  B23P15/02

Abstract: A method of removing excess MCrAIY overlay coating from within a cooling hole of an aluminide coated gas turbine engine component is disclosed. The method includes providing a gas turbine engine component having an internal surface (4), an outer surface (6) and a root end (8). The component also includes at least one cooling hole (10) extending from the internal surface (4) to the outer surface (6), wherein the internal surface(4) of the component is coated with a corrosion resistant aluminide coating. An MCrAIY overlay coating (12) is also located on the outer surface (6) and inside a portion of the cooling hole (10). An abrasive slurry is forced into the gas turbine engine component from the outside of the component to the inside of the component, through the cooling hole (10), such that the slurry flows through the internal surface (4) of the component and removes at least a portion of the overlay coating (12) located inside the cooling hole (10) without adversely affecting the internal surface (4) of the component. The abrasive slurry subsequently exits the component through the root end (8).