Patent US4901522A successfully refreshed from Google Patents.
US4901522A
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US
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Turbojet engine combustion chamber with a double wall converging zone
Assignee: Safran Aircraft Engines SAS
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Filing: 1988-12-09
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Granted: 1990-02-20
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Expires: 2008-12-09
Abstract
Abstract The combustion chamber according to the present invention utilizes a double-walled structure only in the converging portion of the combustion chamber. A hot wall is retained adjacent to, but spaced from a corresponding cold wall so as to provide a cooling space between them. An upstream portion of the hot wall is retained in a notch defined by the cold wall, while the downstream portions each have generally radially extending flanges. Studs pass through openings in the adjacent flanges to prevent any relative circumferential movement, while a clamp serves to attach the flanges to the inlet of a turbine. The clamp slidably retains the flanges therein so as to permit relative radial movement to accommodate any thermal expansion and contraction of the combustion chamber, solely by the appended claims.
Inventors
- 👤 Patrice Commaret
- 👤 Michel A. A. Desaulty
- 👤 Didier H. Hernandez
- 👤 Jean-Claude Laugeois
- 👤 Gerard M. F. Mandet
- 👤 Rodolphe Martinez
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-04 14:26
CPC Classifications
F; F23; F23R; F23R3/00; F23R3/02; F23R3/04; F23R3/06; F23R3/08; F23R3/002; F05; F05B; F05B2260/00; F05B2260/20; F05B2260/201; F05B2260/202; Y; Y02; Y02T; Y02T50/00; Y02T50/60
Claims Analysis
Total Claims: 9
Claim 1
Independent Claim
325 words
In a turbojet engine having a turbine section, the improved annular combustion chamber having a combustion zone, a dilution zone and convergent zone comprising: (a) a single thickness first outer annular wall defining a radially outer boundary of the combustion zone and the dilution zone; (b) a single thickness first inner annular wall defining a radially inner boundary of the combustion zone and the dilution zone; (c) a double thickness, second outer annular wall defining a radially outer boundary of the convergent zone and connected to the single thickness outer annular wall comprising: (i) a first cold wall having a first flange extending radially from a downstream edge; and, (ii) a first hot wall disposed adjacent to but spaced radially inwardly of the first cold wall, and having a second flange extending radially from a downstream edge; (d) first attaching means to attach the first and second flanges to the turbine section so as to allow relative radial movement between the flanges and the turbine section; (e) a double thickness second inner annular wall defining a radially inner boundary of the convergent zone and connected to the single thickness inner annular wall comprising: (i) a second cold wall having a third flange extending radially from a downstream edge; and, (ii) a second hot wall disposed adjacent to but spaced radially outwardly of the second cold wall, and having a fourth flange extending radially from a downstream edge; (f) second attaching means to attach the third and fourth flanges to the turbine section so as to allow relative radial movement between the flanges and the turbine section; (g) a plurality of bores defined by the first, second, third and fourth flanges; and, (h) a plurality of generally cylindrical studs extending into the bores between the first and second flanges, and between the third and fourth flanges so as to prevent relative circumferential movement between the first and second flanges, and the third and fourth flanges, respectively.
Claim 2
Dependent Claim
325 words
In a turbojet engine having a turbine section, the improved annular combustion chamber having a combustion zone, a dilution zone and convergent zone comprising: (a) a single thickness first outer annular wall defining a radially outer boundary of the combustion zone and the dilution zone; (b) a single thickness first inner annular wall defining a radially inner boundary of the combustion zone and the dilution zone; (c) a double thickness, second outer annular wall defining a radially outer boundary of the convergent zone and connected to the single thickness outer annular wall comprising: (i) a first cold wall having a first flange extending radially from a downstream edge; and, (ii) a first hot wall disposed adjacent to but spaced radially inwardly of the first cold wall, and having a second flange extending radially from a downstream edge; (d) first attaching means to attach the first and second flanges to the turbine section so as to allow relative radial movement between the flanges and the turbine section; (e) a double thickness second inner annular wall defining a radially inner boundary of the convergent zone and connected to the single thickness inner annular wall comprising: (i) a second cold wall having a third flange extending radially from a downstream edge; and, (ii) a second hot wall disposed adjacent to but spaced radially outwardly of the second cold wall, and having a fourth flange extending radially from a downstream edge; (f) second attaching means to attach the third and fourth flanges to the turbine section so as to allow relative radial movement between the flanges and the turbine section; (g) a plurality of bores defined by the first, second, third and fourth flanges; and, (h) a plurality of generally cylindrical studs extending into the bores between the first and second flanges, and between the third and fourth flanges so as to prevent relative circumferential movement between the first and second flanges, and the third and fourth flanges, respectively.
Claim 3
Dependent Claim
76 words
The improved combustion chamber according to claim 1 wherein the first attaching means comprises: (a) a fifth flange extending generally axially from the turbine section; and (b) a first clamp defining a first, radially opening groove dimensioned so as to slidably receive at least a portion of the first and second flanges so as to prevent any substantial axial movement therebetween, and defining a second, axially opening groove dimensioned so as to receive the fifth flange.
Claim 4
Dependent Claim
76 words
The improved combustion chamber according to claim 2 wherein the second attaching means comprises: (a) a sixth flange extending generally axially from the turbine section; and (b) a second clamp defining a third, radially opening groove dimensioned so as to slidably receive at least a portion of the third and fourth flanges so as to prevent any substantial axial movement therebetween, and defining a fourth, axially opening groove dimensioned so as to receive the sixth flange.
Claim 5
Dependent Claim
56 words
The improved combustion chamber according to claim 3 wherein the radial dimensions of the first and third radially opening grooves are greater than radial dimensions of the first, second, third and fourth flanges so as to allow radial movement of the first and second hot and cold walls with respect to the first and second clamps.
Claim 6
Dependent Claim
53 words
The improved combustion chamber according to claim 1 wherein the first and second cold walls each define a notch adjacent an upstream edge and wherein the first and second hot walls each comprise a plurality of arcuate segments, each segment having an upstream edge portion engaging the notch in the respective cold wall.
Claim 7
Dependent Claim
76 words
The improved combustion chamber according to claim 5 further comprising: (a) a plurality of first cooling perforations defined by a downstream portion of the first and second cold walls, respectively to allow cooling air to enter the space between the respective hot and cold walls; and (b) evacuation orifices defined by upstream portions of the first and second hot walls to permit evacuation of the cooling air in the space between the hot and cold walls.
Claim 8
Dependent Claim
49 words
The improved combustion chamber according to claim 6 further comprising a generally axially extending lip formed on an upstream portion of each cold wall and extending generally axially adjacent the evacuation orifices so as to direct air passing through the orifices along a surface of the respective hot wall.
Claim 9
Dependent Claim
42 words
The improved combustion chamber according to claim 7 further comprising a plurality of second cooling perforations defined by a downstream portion of each hot wall, the second cooling perforations located so as to be out of alignment with the first cooling perforations.
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USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1993-02-19 | 1993-08-21 | 1994-02-20 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1997-02-19 | 1997-08-21 | 1998-02-20 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2001-02-19 | 2001-08-21 | 2002-02-20 | $7700.00 | Window Closed / Lapsed |