公开(公告)号：JP2001207866A

公开(公告)日：2001-08-03

申请号：JP2000383063

申请日：2000-12-18

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DALZELL WILLIAM JOHN JR ,  SANDERS STUART ALAN ,  CRAWFORD GEORGE LEE ,  WALDEN FREDERICK CLELL ,  WOODARD WILLIAM J

IPC: F01D11/02 ,  F01D11/08 ,  F01D11/12 ,  F02C7/00 ,  F02C7/28 ,  F04D29/02 ,  F04D29/08 ,  F04D29/10 ,  F04D29/54 ,  F16J15/453

Abstract: PROBLEM TO BE SOLVED: To provide an air seal for a gas turbine engine having performance excellent more than a conventional air seal by using a conventional device. SOLUTION: This method of forming the air seal for the gas turbine engine includes the performance of plasma spraying of an abradable seal layer 38 on a base material 30 by preparing the seal base material 30, and this plasma spraying includes the performance of spraying of a bulk material of a thermosetting polymer and a thermoplastic binder material. The method of forming the air seal in another form includes adhering of this molded seal material to the seal base material 30 by removing the molded seal material by molding the abradable layer 38 including the thermosetting polymer and the thermoplastic material by preparing the seal base material 30.

公开(公告)号：JP2001207865A

公开(公告)日：2001-08-03

申请号：JP2000383062

申请日：2000-12-18

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DALZELL WILLIAM JOHN JR ,  SANDERS STUART ALAN ,  CRAWFORD GEORGE LEE ,  WALDEN FREDERICK CLELL ,  WOODARD WILLIAM J

IPC: F01D11/02 ,  F01D11/08 ,  F01D11/12 ,  F02C7/00 ,  F02C7/28 ,  F04D29/02 ,  F04D29/08 ,  F04D29/10 ,  F04D29/54 ,  F16J15/453

Abstract: PROBLEM TO BE SOLVED: To provide an air seal for a gas turbine engine having performance excellent more than a conventional air seal. SOLUTION: This air seal for the gas turbine engine includes a seal base material 30 and an abradable seal layer 38 arranged on this base material 30. This abradable seal layer 38 includes at least a bulk material of a thermosetting polymer such as phenol powder and a thermoplastic binder material such as PEEK. This abradable layer 38 can include a filler so as to have desired characteristics such as porosity becoming easily abrasive and dry lubricity.

公开(公告)号：JP2000186574A

公开(公告)日：2000-07-04

申请号：JP36051499

申请日：1999-12-20

Applicant: UNITED TECHNOLOGIES CORP

Inventor： WALDEN FREDERICK CLELL ,  CRAWFORD GEORGE LEE ,  DALZELL WILLIAM JOHN JR

IPC: F02C7/28 ,  C23C4/04 ,  C23C4/18 ,  F01D5/28 ,  F01D11/12 ,  F16J15/40

Abstract: PROBLEM TO BE SOLVED: To provide a seal having no fear of firing occurring in a state to peel quantities of seal materials from a seal. SOLUTION: A seal is provided with a seal base 30 and a thermally sprayed metal adhesion layer 36. The metal adhesion layer 36 is formed at least at a part of the seal base 30. The metal adhesion layer 36 contains preferably thermally sprayed nickel and aluminum, and up to 1 wt.% of each of iron, copper, zinc, manganese, and magnesium. The seal layer further has a wear layer 38 and the seal layer is applied on the metal adhesion layer 36. The seal layer is that aluminum powder and silicon powder, forming a metallic substrate, are thermally sprayed on the seal layer, and a polymer buried in the substrate, for example, filler particles of methyl methacrylate, buried in the substrate, is accumulated simultaneously therewith. Firing ability in a state that an extremely large quantity of seal materials are peeled from a seal is lowered by filler particle.

公开(公告)号：DE69926858D1

公开(公告)日：2005-09-29

申请号：DE69926858

申请日：1999-12-14

Applicant: UNITED TECHNOLOGIES CORP

Inventor： WALDEN FREDERICK CLELL ,  CRAWFORD GEORGE LEE ,  DALZELL JR

IPC: F02C7/28 ,  C23C4/04 ,  C23C4/18 ,  F01D5/28 ,  F01D11/12 ,  F16J15/40 ,  C23C4/02

Abstract: An air seal for use in a gas turbine engine includes reduced susceptibility to deflagration during operating conditions in which an excessive amount of seal material is liberated from the seal and ingested into the engine. The seal includes a seal substrate 30, and a thermally sprayed metallic bond layer 36 applied to the seal substrate 30. The bond layer 30 includes nickel and aluminum. The seal also includes a thermally sprayed abradable seal layer 38 applied to the bond layer36. The abradable material is composed of aluminum powder and silicon powder forming a metal matrix, and co-deposited methyl methacrylate particles embedded as filler in the metal matrix. The filler is less likely to deflagrate compared to conventionally used materials such as polyester.

公开(公告)号：DE60027258T2

公开(公告)日：2007-01-18

申请号：DE60027258

申请日：2000-12-04

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DALZELL WILLIAM JOHN ,  CRAWFORD GEORGE LEE ,  WOODARD WILLIAM J ,  SANDERS STUART ALAN ,  WALDEN FREDERICK CLELL

IPC: F01D11/02 ,  F01D11/12 ,  F01D11/08 ,  F02C7/00 ,  F02C7/28 ,  F04D29/02 ,  F04D29/08 ,  F04D29/10 ,  F04D29/54 ,  F16J15/453

公开(公告)号：DE69926858T2

公开(公告)日：2006-06-22

申请号：DE69926858

申请日：1999-12-14

Applicant: UNITED TECHNOLOGIES CORP

Inventor： WALDEN FREDERICK CLELL ,  CRAWFORD GEORGE LEE ,  DALZELL WILLIAM JOHN

IPC: F01D11/12 ,  F02C7/28 ,  C23C4/02 ,  C23C4/04 ,  C23C4/18 ,  F01D5/28 ,  F16J15/40

Abstract: An air seal for use in a gas turbine engine includes reduced susceptibility to deflagration during operating conditions in which an excessive amount of seal material is liberated from the seal and ingested into the engine. The seal includes a seal substrate 30, and a thermally sprayed metallic bond layer 36 applied to the seal substrate 30. The bond layer 30 includes nickel and aluminum. The seal also includes a thermally sprayed abradable seal layer 38 applied to the bond layer36. The abradable material is composed of aluminum powder and silicon powder forming a metal matrix, and co-deposited methyl methacrylate particles embedded as filler in the metal matrix. The filler is less likely to deflagrate compared to conventionally used materials such as polyester.

公开(公告)号：DE60027258D1

公开(公告)日：2006-05-24

申请号：DE60027258

申请日：2000-12-04

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DALZELL JR ,  CRAWFORD GEORGE LEE ,  WOODARD WILLIAM J ,  SANDERS STUART ALAN ,  WALDEN FREDERICK CLELL

IPC: F01D11/02 ,  F01D11/12 ,  F01D11/08 ,  F02C7/00 ,  F02C7/28 ,  F04D29/02 ,  F04D29/08 ,  F04D29/10 ,  F04D29/54 ,  F16J15/453

公开(公告)号：AT302896T

公开(公告)日：2005-09-15

申请号：AT99310049

申请日：1999-12-14

Applicant: UNITED TECHNOLOGIES CORP

Inventor： WALDEN FREDERICK CLELL ,  CRAWFORD GEORGE LEE ,  DALZELL WILLIAM JOHN JR

IPC: F02C7/28 ,  C23C4/04 ,  C23C4/18 ,  F01D5/28 ,  F01D11/12 ,  F16J15/40 ,  C23C4/02

Abstract: An air seal for use in a gas turbine engine includes reduced susceptibility to deflagration during operating conditions in which an excessive amount of seal material is liberated from the seal and ingested into the engine. The seal includes a seal substrate 30, and a thermally sprayed metallic bond layer 36 applied to the seal substrate 30. The bond layer 30 includes nickel and aluminum. The seal also includes a thermally sprayed abradable seal layer 38 applied to the bond layer36. The abradable material is composed of aluminum powder and silicon powder forming a metal matrix, and co-deposited methyl methacrylate particles embedded as filler in the metal matrix. The filler is less likely to deflagrate compared to conventionally used materials such as polyester.