Patent US4787209A successfully refreshed from Google Patents.
US4787209A
Expired / Lapsed
US
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Stacked ring combustor assembly
Assignee: Honeywell International Inc
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Filing: 1988-04-20
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Granted: 1988-11-29
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Expires: 2008-04-20
Abstract
Abstract An assembly of stacked rings is provided to form the cylindrical section of a combustor such as used in a gas turbine engine. Each ring is force-fitted into its adjacent ring and joined to it, as by brazing, to form a unitary structure. The rings are configured to assure proper alignment when fitted together and provide a space for holding brazing material immediately adjacent to the mating surfaces to be joined so that the brazing material, when fused in a vacuum furnace, flows evenly between the surfaces. To assure proper distribution of the brazing material when fused, one of the mating surfaces may be upset, as by knurling, to a dimension assuring a light force-fit of the parts to be joined. Each ring also includes a shaped portion projecting into the interior of the assembly for directing cooling air, introduced through the side walls of the rings, along the interior surfaces of the assembly to protect it from high temperature gases generated by combustion of fuel within the combustor.
Inventors
- 👤 Charles R. Taylor
- 👤 George Opdyke, Jr.
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-26 23:29
CPC Classifications
B; B23; B23K; B23K1/00; B23K1/14; B23K1/18; F; F23; F23R; F23R3/00; F23R3/002; F23R3/02; F23R3/04; F23R3/06; F23R3/08; B23K2101/00; B23K2101/001; F05; F05B; F05B2260/00; F05B2260/20; F05B2260/202
Claims Analysis
Total Claims: 5
Claim 1
Independent Claim
241 words
A combustor assembly for gas turbine engines comprising: a plurality of generally annular members having a common center line, each such member having at one end a first cylindrical portion having a cylindrical inner surface concentric about said center line, a second axially inwardly tapered portion at the other end, and a third step-shaped portion intermediate said first and second portions, each said step-shaped portion having a cylindrical first surface concentric about said center line and a second surface normal to said center line defining said step, said annular members being disposed in nested substantially coaxial relationship spaced axially along said center line with at lest a portion of said first cylindrical portions nested in said third step portions, said inner surfaces of said first portions facing said first surfaces, said first and second portions being disposed in overlapping relationship, said first cylindrical portions having holes therein which in combination with said overlapping first and second portions define airflow passages, said first and third portions defining a substantially smooth outer wall, each said first surface having a machined diameter just slightly less than the inside diameter of each said first cylindrical portion, one of said facing first portion inner surfaces and said first surfaces being upset to define at a plurality of different locations portions of said upset surface in contact with said inner surface; and brazing material disposed between and bonding said first portion inner surfaces and said first surfaces.
Claim 2
Dependent Claim
241 words
A combustor assembly for gas turbine engines comprising: a plurality of generally annular members having a common center line, each such member having at one end a first cylindrical portion having a cylindrical inner surface concentric about said center line, a second axially inwardly tapered portion at the other end, and a third step-shaped portion intermediate said first and second portions, each said step-shaped portion having a cylindrical first surface concentric about said center line and a second surface normal to said center line defining said step, said annular members being disposed in nested substantially coaxial relationship spaced axially along said center line with at lest a portion of said first cylindrical portions nested in said third step portions, said inner surfaces of said first portions facing said first surfaces, said first and second portions being disposed in overlapping relationship, said first cylindrical portions having holes therein which in combination with said overlapping first and second portions define airflow passages, said first and third portions defining a substantially smooth outer wall, each said first surface having a machined diameter just slightly less than the inside diameter of each said first cylindrical portion, one of said facing first portion inner surfaces and said first surfaces being upset to define at a plurality of different locations portions of said upset surface in contact with said inner surface; and brazing material disposed between and bonding said first portion inner surfaces and said first surfaces.
Claim 3
Dependent Claim
23 words
An assembly for a combustor as described in claim 1 in which the upset portions define interconnected spaces for holding said brazing material.
Claim 4
Dependent Claim
39 words
An assembly for a combustor as described in claim 2 in which the radial dimension of said spaces are substantially the same whereby prior to brazing said annular members are each substantially fixedly held concentric about said center line.
Claim 5
Dependent Claim
21 words
An assembly for a combustor as described in claim 3 in which said upset portions and spaces define a knurled surface.
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) | 1991-11-29 | 1992-05-30 | 1992-11-29 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1995-11-29 | 1996-05-30 | 1996-11-29 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1999-11-29 | 2000-05-30 | 2000-11-29 | $7700.00 | Window Closed / Lapsed |