US4257735A — Gas turbine engine seal and method for making same

Claim 1

Independent Claim 123 words

A composite article for use in a seal in a gas turbine engine, said seal including a face seal adapted to cooperate with a rotating edge to prevent the passage of fluid from a first zone to a second zone in said engine, said composite article comprising: a substrate of sintered metallic fibers and having an apparent density within the range of 14.0% to 22.5%, said substrate including a network of interconnected pores and metallic bonds at points of contact between said fibers, said substrate further including an external face having surface pores in communication with said network; and a thin film barrier surface layer impervious to the passage of fluid, said layer disposed on said external face and filling said surface pores.

Claim 2

Dependent Claim 123 words

A composite article for use in a seal in a gas turbine engine, said seal including a face seal adapted to cooperate with a rotating edge to prevent the passage of fluid from a first zone to a second zone in said engine, said composite article comprising: a substrate of sintered metallic fibers and having an apparent density within the range of 14.0% to 22.5%, said substrate including a network of interconnected pores and metallic bonds at points of contact between said fibers, said substrate further including an external face having surface pores in communication with said network; and a thin film barrier surface layer impervious to the passage of fluid, said layer disposed on said external face and filling said surface pores.

Claim 3

Dependent Claim 22 words

The invention as set forth in claim 1 wherein said thin film barrier surface layer is comprised of a silicone base resin.

Claim 4

Dependent Claim 119 words

A seal for preventing the flow of fluid between zones in a gas turbine engine, said seal comprising: a composite face seal having a porous substrate formed by sintered metallic fibers and having an apparent density within the range of 14.0% to 22.5%, said substrate further including a network of interconnected pores and an external face having surface pores in communication with said network, said composite face seal further including a thin film surface layer disposed on said substrate and filling said surface pores, said layer comprising a barrier impervious to the passage of fluid; and a rotating edge disposed immediately proximate to said face seal and adapted to form a groove in said face seal during engine operation.

Claim 5

Dependent Claim 119 words

A seal for preventing the flow of fluid between zones in a gas turbine engine, said seal comprising: a composite face seal having a porous substrate formed by sintered metallic fibers and having an apparent density within the range of 14.0% to 22.5%, said substrate further including a network of interconnected pores and an external face having surface pores in communication with said network, said composite face seal further including a thin film surface layer disposed on said substrate and filling said surface pores, said layer comprising a barrier impervious to the passage of fluid; and a rotating edge disposed immediately proximate to said face seal and adapted to form a groove in said face seal during engine operation.

Claim 6

Dependent Claim 17 words

The invention as set forth in claim 3 wherein said surface layer is comprised of silicone resin.

Claim 7

Dependent Claim 19 words

The invention as set forth in claim 4 wherein said surface layer is further comprised of a metallic filler.

Claim 8

Dependent Claim 17 words

The invention as set forth in claim 5 wherein said surface layer is comprised of aluminum silicone.

Claim 9

Dependent Claim 46 words

The invention as set forth in claim 3 wherein said thin film surface layer is comprised of a first chemical state and said groove is formed in said face seal by said edge during initial engine operation while said layer is in said first chemical state.

Claim 10

Dependent Claim 24 words

The invention as set forth in claim 7 wherein said surface layer transforms to a second chemical state while said engine accumulates running time.

Claim 11

Dependent Claim 25 words

The invention as set forth in claim 8 wherein said transformation occurs in response to a temperature in said engine during said accumulated running time.

Claim 12

Independent Claim 131 words

A method of providing a seal for preventing the flow of fluid between zones in a gas turbine engine, said method comprising the steps of: constructing a substrate formed of sintered metallic fibers and having an apparent density within the range 14.0% to 22.5%; disposing a thin film surface layer on said substrate to form a composite face seal, said surface layer impervious to the passage of fluid; initially curing said surface layer; installing said face seal in said engine immediately proximate a rotating edge; operating the engine on an initial cycle to cause said rotating edge to form a groove in said surface layer; and transforming said surface layer during engine accumulated running time from a first chemical state to a second chemical state in response to an engine temperature.

Claim 13

Independent Claim 131 words

A method of providing a seal for preventing the flow of fluid between zones in a gas turbine engine, said method comprising the steps of: constructing a substrate formed of sintered metallic fibers and having an apparent density within the range 14.0% to 22.5%; disposing a thin film surface layer on said substrate to form a composite face seal, said surface layer impervious to the passage of fluid; initially curing said surface layer; installing said face seal in said engine immediately proximate a rotating edge; operating the engine on an initial cycle to cause said rotating edge to form a groove in said surface layer; and transforming said surface layer during engine accumulated running time from a first chemical state to a second chemical state in response to an engine temperature.

Claim 14

Dependent Claim 25 words

The invention as set forth in claim 10 wherein said disposing step includes disposing a thin film surface layer comprised of a silicone based resin.

Claim 15

Dependent Claim 30 words

The invention as set forth in claim 11 wherein said transforming step includes transforming said surface layer to a second chemical state wherein said surface layer is comprised of silica.

Annuity Stage	Window Opens	Payment Deadline	Surcharge Period Until	Estimated Fee	Status
3.5 Years (Year 4)	1984-03-23	1984-09-22	1985-03-24	$2000.00	Window Closed / Lapsed
7.5 Years (Year 8)	1988-03-23	1988-09-22	1989-03-24	$3760.00	Window Closed / Lapsed
11.5 Years (Year 12)	1992-03-23	1992-09-22	1993-03-24	$7700.00	Window Closed / Lapsed

Gas turbine engine seal and method for making same

Abstract

Inventors

Bibliographic Details

Claims Analysis

References Cited (Backward Citations)

USPTO Annuity & Maintenance Windows

Assigned Categories & Tags

Assign Category Tag