US3906718A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Combustion apparatus for gas turbine engines
Assignee: Rolls Royce PLC
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Filing: 1973-09-04
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Granted: 1975-09-23
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Expires: 1993-09-04
Abstract
Abstract A combustion chamber for a gas turbine engine which has staged combustion in two toroidal vortices of opposite hand arranged one upstream of the other. A burner delivers air/fuel mixture in a radial direction to support the vortices and the burner has a convergent outlet for the air/fuel mixture.
Inventors
- 👤 Robert David Wood
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-25 19:39
CPC Classifications
F; F23; F23R; F23R3/00; F23R3/02; F23R3/04; F23R3/10; F23R3/12; F23R3/28; F23R3/286; Y; Y02; Y02T; Y02T50/00; Y02T50/60
Claims Analysis
Total Claims: 4
Claim 1
Independent Claim
233 words
Combustion apparatus comprising: a combustion chamber having an upstream end wall and a downstream wall, openings in said chamber walls defining first and second air inlet means for delivering air into said chamber, a member extending axially downstream of said upstream end wall defining at least in part a passage which is in communication with said first air inlet means, means for supplying fuel to the passage, a deflecting member disposed for deflecting the air/fuel mixture at the downstream end of the passage in a direction substantially radially of said passage whereby to promote a substantially toroidal vortex circulating first radially outward from said passage, then upstream toward the upstream end wall of the combustion chamber and then downstream adjacent and substantially parallel to the passage, said secondary air inlet means being positioned to promote a secondary toroidal vortex immediately downstream of said first vortex and having a hand opposite to that of said first vortex, said member defining said passage being a cylindrical member which forms with said deflecting member an annular outlet, and a plurality of axially extending straight dividers which divide the passage into a plurality of axially extending straight sectors and which prevent swirl in the air/fuel mixture passing through the passage sectors wherein said outlet converges radially around its circumference and terminates in an annular discharge opening through which the air/fuel mixture is discharged into the combustion chamber.
Claim 2
Dependent Claim
233 words
Combustion apparatus comprising: a combustion chamber having an upstream end wall and a downstream wall, openings in said chamber walls defining first and second air inlet means for delivering air into said chamber, a member extending axially downstream of said upstream end wall defining at least in part a passage which is in communication with said first air inlet means, means for supplying fuel to the passage, a deflecting member disposed for deflecting the air/fuel mixture at the downstream end of the passage in a direction substantially radially of said passage whereby to promote a substantially toroidal vortex circulating first radially outward from said passage, then upstream toward the upstream end wall of the combustion chamber and then downstream adjacent and substantially parallel to the passage, said secondary air inlet means being positioned to promote a secondary toroidal vortex immediately downstream of said first vortex and having a hand opposite to that of said first vortex, said member defining said passage being a cylindrical member which forms with said deflecting member an annular outlet, and a plurality of axially extending straight dividers which divide the passage into a plurality of axially extending straight sectors and which prevent swirl in the air/fuel mixture passing through the passage sectors wherein said outlet converges radially around its circumference and terminates in an annular discharge opening through which the air/fuel mixture is discharged into the combustion chamber.
Claim 3
Dependent Claim
234 words
Combustion apparatus comprising a combustion chamber having an upstream end wall and a downstream wall, openings in said chamber walls defining first and second air inlet means for delivering air into said chamber, a member extending axially downstream of said upstream end wall and defining at least in part a passage which is in communication with said first air inlet means, means for supplying a fuel to said passage, a deflecting member disposed for deflecting the air/fuel mixture at the downstream end of the passage in a direction substantially radially of said passage to thereby promote a substantially toroidal vortex circulating first radially outward from said passage, then upstream toward the upstream end wall of the combustion chamber and then downstream adjacent and substantially parallel to said passage, said secondary air inlet means being positioned to promote a secondary toroidal vortex immediately downstream of said first vortex and having a hand opposite to that of said first vortex, said member defining said passage including a plurality of axially extending straight dividers which divide the passage into a plurality of axially extending straight sectors and which prevent swirl in the air/fuel mixture passing along the passage sectors, said member defining said passage forming with said deflecting member an outlet wherein said outlet converges radially about its circumference and terminates in a circumferential discharge opening through which the air/fuel mixture is discharged into the combustion chamber.
Claim 4
Dependent Claim
234 words
Combustion apparatus comprising a combustion chamber having an upstream end wall and a downstream wall, openings in said chamber walls defining first and second air inlet means for delivering air into said chamber, a member extending axially downstream of said upstream end wall and defining at least in part a passage which is in communication with said first air inlet means, means for supplying a fuel to said passage, a deflecting member disposed for deflecting the air/fuel mixture at the downstream end of the passage in a direction substantially radially of said passage to thereby promote a substantially toroidal vortex circulating first radially outward from said passage, then upstream toward the upstream end wall of the combustion chamber and then downstream adjacent and substantially parallel to said passage, said secondary air inlet means being positioned to promote a secondary toroidal vortex immediately downstream of said first vortex and having a hand opposite to that of said first vortex, said member defining said passage including a plurality of axially extending straight dividers which divide the passage into a plurality of axially extending straight sectors and which prevent swirl in the air/fuel mixture passing along the passage sectors, said member defining said passage forming with said deflecting member an outlet wherein said outlet converges radially about its circumference and terminates in a circumferential discharge opening through which the air/fuel mixture is discharged into the combustion chamber.
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) | 1978-09-22 | 1979-03-24 | 1979-09-23 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1982-09-22 | 1983-03-24 | 1983-09-23 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1986-09-22 | 1987-03-24 | 1987-09-23 | $7700.00 | Window Closed / Lapsed |