US4498617A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Method for reshaping a gas turbine engine combustor part
Assignee: RTX Corp
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Filing: 1983-03-31
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Granted: 1985-02-12
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Expires: 2003-03-31
Abstract
Abstract A combustor liner for a gas turbine engine, which has become distorted during use or repair, is restored to its original dimensions by selective heating at two circular locations, accompanied by outward radial replacement. An induction coil is used to heat the liner. When the support ring parts are also replaced, the high temperature mechanical reforming procedure is such that the subsequent distortion which accompanies the welding replacement of support rings is compensated for.
Inventors
- 👤 Joseph J. Guertin
- 👤 Earl J. Provencal
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-31 13:44
CPC Classifications
B; B23; B23P; B23P6/00; B23P6/002; B23P6/005; F; F02; F02C; F02C7/00; F02C7/28; B23K; B23K13/00; F23; F23R; F23R3/00
Claims Analysis
Total Claims: 7
Claim 1
Independent Claim
161 words
The method of shaping an annular combustor liner made of a high temperature alloy and usable in a gas turbine engine, wherein the liner is comprised of a generally cylindrical wall section centered about an axis, a circular flange section attached to the cylindrical wall section and extending generally transverse to the axis, and a plurality of circumferentially spaced apart rings attached to the flange, each defining an opening through the flange which is suitable for receiving a fuel nozzle or the like; which method comprises simultaneously heating a first circumferential band of the liner where the wall section joins the flange section and a second circumferential band around the flange on the opposing side of the rings from the first band; and while the bands are heated, moving the rings generally radially with respect to the axis to a position displaced from their start position, and then cooling the heated band regions while holding the rings in their displaced position.
Claim 2
Independent Claim
161 words
The method of shaping an annular combustor liner made of a high temperature alloy and usable in a gas turbine engine, wherein the liner is comprised of a generally cylindrical wall section centered about an axis, a circular flange section attached to the cylindrical wall section and extending generally transverse to the axis, and a plurality of circumferentially spaced apart rings attached to the flange, each defining an opening through the flange which is suitable for receiving a fuel nozzle or the like; which method comprises simultaneously heating a first circumferential band of the liner where the wall section joins the flange section and a second circumferential band around the flange on the opposing side of the rings from the first band; and while the bands are heated, moving the rings generally radially with respect to the axis to a position displaced from their start position, and then cooling the heated band regions while holding the rings in their displaced position.
Claim 3
Dependent Claim
68 words
The method of claim 1 which comprises detaching the rings from the liner after they are moved to their displaced position; and fixturing and welding in their place new rings of approximately equal dimension, the welding inducing strains which cause the new rings to move to a new radial position which lies generally along the path traveled by the old rings during their movement to the displaced position.
Claim 4
Dependent Claim
35 words
The method of claim 1 characterized by heating the bands using two circumferential electrical conductors carrying high frequency current, where a circumferential conductor is placed in proximity to each of the inner and outer bands.
Claim 5
Dependent Claim
14 words
The method of claim 1 wherein the rings are restrained from any vertical motion.
Claim 6
Dependent Claim
29 words
The method of claim 1 wherein the liner is constructed of a wrought non-hardening high temperature nickel alloy and wherein the bands are heated to at least 1800° F.
Claim 7
Dependent Claim
28 words
The method of claim 5 characterized by heating the bands to 1800° F. in steps, first to 1600° F., then to 1700° F. and then to 1800° F.
References Cited (Backward Citations)
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1988-02-12 | 1988-08-13 | 1989-02-12 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1992-02-12 | 1992-08-13 | 1993-02-12 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1996-02-12 | 1996-08-13 | 1997-02-12 | $7700.00 | Window Closed / Lapsed |