Patent US4449714A successfully refreshed from Google Patents.
US4449714A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Turbine engine seal and method for repair thereof
Assignee: KLOCK OF DELAWARE Inc
•
Filing: 1983-03-22
•
Granted: 1984-05-22
•
Expires: 2003-03-22
Abstract
Abstract A method for repairing turbine engine seals and a product manufactured in accordance with the method are provided. A worn or damaged honeycomb seal is removed from a backing plate together with a portion of the surface of the plate. The plate is restored to substantially its original thickness by a low pressure plasma spraying operation which may be followed by further machining to arrive at the required plate thickness. A new seal is then brazed thereon. The finished product will include the backing plate, a low pressure plasma sprayed coated surface, and a honeycomb seal brazed to the coated surface.
Inventors
- 👤 John W. Meier
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-04 07:44
CPC Classifications
B; B23; B23P; B23P6/00; B23P6/002; Y; Y10; Y10S; Y10S277/00; Y10S277/922; Y10T; Y10T29/00; Y10T29/49; Y10T29/49718; Y10T29/49719; Y10T29/49721; Y10T29/49723; Y10T29/49725; Y10T29/49726; Y10T29/49728
Claims Analysis
Total Claims: 23
Claim 1
Independent Claim
60 words
A method for repairing or constructing a seal assembly of the type having a backing plate and a seal attached thereto, comprising the steps of low pressure plasma spraying a surface of a backing wall of said backing plate to provide a coating thereon and increase the thickness of said backing wall, and attaching said seal to said coated surface.
Claim 2
Independent Claim
60 words
A method for repairing or constructing a seal assembly of the type having a backing plate and a seal attached thereto, comprising the steps of low pressure plasma spraying a surface of a backing wall of said backing plate to provide a coating thereon and increase the thickness of said backing wall, and attaching said seal to said coated surface.
Claim 3
Dependent Claim
23 words
A method as defined in claim 1 including the step of roughing said surface of said backing wall prior to the spraying thereof.
Claim 4
Dependent Claim
23 words
A method as defined in claim 2 including the step of removing a portion of said coating prior to applying said seal thereon.
Claim 5
Dependent Claim
23 words
A method as defined in claim 1 including the step of removing a portion of said coating prior to applying said seal thereon.
Claim 6
Dependent Claim
18 words
A method as defined in claim 1 including the step of brazing said seal to said coated surface.
Claim 7
Dependent Claim
14 words
A method as defined in claim 5 wherein said seal is a honeycomb seal.
Claim 8
Dependent Claim
20 words
A method as defined in claim 6 including the step of preheating said backing plate prior to the spraying thereof.
Claim 9
Dependent Claim
22 words
A method as defined in claim 7 including the step of reverse transferred arc cleaning said backing plate prior to plasma spraying.
Claim 10
Dependent Claim
23 words
A method as defined in claim 1 wherein said seal assembly is a high pressure turbine seal segment of a gas turbine engine.
Claim 11
Dependent Claim
18 words
A method as defined in claim 9 wherein said surface of said backing wall is sprayed with HASTALLOY-X.
Claim 12
Dependent Claim
26 words
A method as defined in claim 10 wherein said seal is a honeycomb seal, and including the step of brazing said seal to said coated surface.
Claim 13
Independent Claim
93 words
A method for repairing a worn or damaged seal of a gas turbine engine, said seal including a backing plate having a backing wall and a honeycomb seal attached to said backing wall, comprising the steps of: removing said honeycomb seal from said backing wall, thereby reducing the thickness of said backing wall; low pressure plasma spraying the surface of said backing wall from which said honeycomb seal was removed, thereby restoring said backing wall to a desired thickness; and applying a new honeycomb seal to said sprayed surface of said backing wall.
Claim 14
Independent Claim
93 words
A method for repairing a worn or damaged seal of a gas turbine engine, said seal including a backing plate having a backing wall and a honeycomb seal attached to said backing wall, comprising the steps of: removing said honeycomb seal from said backing wall, thereby reducing the thickness of said backing wall; low pressure plasma spraying the surface of said backing wall from which said honeycomb seal was removed, thereby restoring said backing wall to a desired thickness; and applying a new honeycomb seal to said sprayed surface of said backing wall.
Claim 15
Dependent Claim
19 words
A method as defined in claim 12 including the step of roughing said surface prior to the spraying thereof.
Claim 16
Dependent Claim
21 words
A method as defined in claim 12 including removing a portion of said sprayed surface prior to applying said honeycomb seal.
Claim 17
Dependent Claim
14 words
A method as defined in claim 12 wherein said surface is sprayed with HASTALLOY-X.
Claim 18
Dependent Claim
18 words
A method as defined in claim 12 including the step of brazing said honeycomb seal to said surface.
Claim 19
Dependent Claim
91 words
A method as defined in claim 12 including the steps of: roughing said surface after removing said honeycomb seal; cleaning said surface after the roughing thereof; loading said backing plate within a low pressure plasma spraying chamber; evacuating said chamber; preheating said backing plate; reverse transferred arc cleaning said backing plate; low pressure plasma spraying said backing plate within said chamber while heated until said desired thickness is obtained; cooling said backing plate; machining said sprayed surface to dimension; and applying said new honeycomb seal to said sprayed and machined surface.
Claim 20
Dependent Claim
36 words
A seal for a turbine engine comprising a backing plate including a backing wall; a low pressure plasma sprayed coating upon said backing wall; and a honeycomb seal attached to said coating upon said backing wall.
Claim 21
Dependent Claim
36 words
A seal for a turbine engine comprising a backing plate including a backing wall; a low pressure plasma sprayed coating upon said backing wall; and a honeycomb seal attached to said coating upon said backing wall.
Claim 22
Dependent Claim
17 words
A seal as defined in claim 18 wherein said coating is up to 35 mils in thickness.
Claim 23
Dependent Claim
12 words
A seal as defined in claim 18 wherein said coating is HASTALLOY-X.
References Cited (Backward Citations)
US2285583A
Cited
US3046648A
Cited
US3918925A
Cited
US4060250A
Cited
GB2001692A
Cited
US4291448A
Cited
US4148494A
Cited
US4336276A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1987-05-22 | 1987-11-21 | 1988-05-22 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1991-05-22 | 1991-11-21 | 1992-05-22 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1995-05-22 | 1995-11-21 | 1996-05-22 | $7700.00 | Window Closed / Lapsed |