US5345768A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Dual-fuel pre-mixing burner assembly
Assignee: General Electric Co
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Filing: 1993-04-07
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Granted: 1994-09-13
•
Expires: 2013-04-07
Abstract
Abstract The burner assembly includes a flow body 12 having a central liquid fuel injection nozzle 14, inner and outer concentric passages 24 and 26, respectively, and a flow duct comprising a venturi downstream of the liquid injection nozzle. The inner passage 24 communicates air and gaseous fuel into the flow duct 16. Swirlers 30 and 38 are provided at the exit ends of the inner and outer passages, respectively, to create counterrotating flows which form a shear layer at the exit of the burner assembly body. The extent of the flow duct 16 facilitates liquid fuel atomization and vaporization, while affording sufficient time for gaseous fuel/air pre-mixing. The arrangement creates a recirculation zone 40 and a shear layer 42 at the exhaust of the burner assembly body which affords flame stabilization.
Inventors
- 👤 Roy M. Washam
- 👤 II Robert A. Corr
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-27 23:14
CPC Classifications
F; F23; F23R; F23R3/00; F23R3/28; F23R3/286; F23C; F23C7/00; F23C7/002; F23C7/004; F23D; F23D17/00; F23D17/002; F23R3/02; F23R3/04; F23R3/10; F23R3/12; F23R3/14; F23R3/36
Claims Analysis
Total Claims: 11
Claim 1
Independent Claim
346 words
A dual-fuel pre-mixing burner assembly for a turbine, comprising: a burner assembly body having an inlet for flowing fuel and air in a generally downstream direction and having a liquid fuel nozzle disposed substantially centrally of and adjacent said inlet to said body for supplying liquid fuel for flow in the generally downstream direction; a flow duct, carried by said body and having an upstream converging section, a throat section and a downstream diverging section, for receiving fuel from central nozzle and air from said inlet; inner and outer generally concentric passages adjacent said body inlet for flowing air through said body; at least one gaseous fuel nozzle carried by said body and located to flow gaseous fuel through said duct in the generally downstream direction; said inner passage lying in communication with said flow duct to supply air thereto for pre-mixing, in said duct, air and fuel from at least one of said central liquid fuel nozzle and said gaseous fuel nozzle to form a lean air fuel mixture and for delivery of said pre-mixed air and fuel to a flow region downstream of said duct; an inner swirler in said inner passage for delivering to said duct air having a flow component in a first tangential direction such that the pre-mixed fuel and air delivered from said duct to said flow region has a flow component in said first tangential direction; said converging section of said duct and said pre-mixed fuel and air, exiting said converging section of said duct, comprising a means for establishing a centerline recirculation zone in said flow region therefore affording flame stabilization; and an outer swirler means in said outer passage for delivering to said flow region downstream of said duct air having a flow component in a second tangential direction generally opposite to said first tangential direction and for establishing, in combination with the flow having said first tangential component, a generally annular shear layer in said flow region, said centerline recirculation zone and said annular shear layer comprising a means for flame stabilization in said burner assembly.
Claim 2
Dependent Claim
346 words
A dual-fuel pre-mixing burner assembly for a turbine, comprising: a burner assembly body having an inlet for flowing fuel and air in a generally downstream direction and having a liquid fuel nozzle disposed substantially centrally of and adjacent said inlet to said body for supplying liquid fuel for flow in the generally downstream direction; a flow duct, carried by said body and having an upstream converging section, a throat section and a downstream diverging section, for receiving fuel from central nozzle and air from said inlet; inner and outer generally concentric passages adjacent said body inlet for flowing air through said body; at least one gaseous fuel nozzle carried by said body and located to flow gaseous fuel through said duct in the generally downstream direction; said inner passage lying in communication with said flow duct to supply air thereto for pre-mixing, in said duct, air and fuel from at least one of said central liquid fuel nozzle and said gaseous fuel nozzle to form a lean air fuel mixture and for delivery of said pre-mixed air and fuel to a flow region downstream of said duct; an inner swirler in said inner passage for delivering to said duct air having a flow component in a first tangential direction such that the pre-mixed fuel and air delivered from said duct to said flow region has a flow component in said first tangential direction; said converging section of said duct and said pre-mixed fuel and air, exiting said converging section of said duct, comprising a means for establishing a centerline recirculation zone in said flow region therefore affording flame stabilization; and an outer swirler means in said outer passage for delivering to said flow region downstream of said duct air having a flow component in a second tangential direction generally opposite to said first tangential direction and for establishing, in combination with the flow having said first tangential component, a generally annular shear layer in said flow region, said centerline recirculation zone and said annular shear layer comprising a means for flame stabilization in said burner assembly.
Claim 3
Dependent Claim
27 words
A burner assembly according to claim 1 wherein said one gaseous fuel nozzle is located adjacent an inlet to said inner passage upstream of said inner swirler.
Claim 4
Dependent Claim
24 words
A burner assembly according to claim 1 wherein said one gaseous fuel nozzle is located in said flow duct downstream of said inner swirler.
Claim 5
Dependent Claim
25 words
A burner assembly according to claim 1 including a gaseous fuel nozzle carried by said body in said outer passage upstream of said outer means.
Claim 6
Dependent Claim
63 words
A burner assembly according to claim 1 wherein said converging section comprising a means for accelerating the flow through said duct, for inhibiting the downstream flame from propagating back toward the fuel nozzles, for affording sufficient time for mixing fuel and air to provide a lean pre-mixed mixture for combustion and for providing a surface for the liquid fuel to impinge and coat.
Claim 7
Dependent Claim
37 words
A burner assembly according to claim 5 wherein said diverging section comprises a means for expanding the flow to a slower velocity, for preventing wall flow separation and for providing an evaporation surface for the liquid fuel.
Claim 8
Dependent Claim
258 words
In a dual-fuel pre-mixing burner assembly for a turbine having a burner assembly body, a liquid fuel nozzle disposed substantially centrally of and adjacent an inlet to said body, a flow duct carried by said body, said duct including an upstream converging section, a throat section and a downstream diverging section, inner and outer generally concentric passages adjacent said body inlet, and at least one gaseous fuel nozzle carried by said body, a method of combustion comprising the steps of: flowing fuel from said liquid fuel injection nozzle into said flow duct for flow in a generally downstream direction; introducing air through said inner passage into said flow duct having flow components in a first generally tangential direction and said generally downstream direction for mixing in said flow duct with said liquid fuel and affording a swirl to the flow exhausting from said diverging section; establishing downstream of said burner body a recirculation zone resultant from expanding the swirling exhaust flow from the diverging section of the flow duct to afford flame stabilization; flowing air through said outer passage bypassing said flow duct into a flow region downstream of said burner body with a flow component in a second generally tangential direction opposite said first tangential direction to establish therewith a shear flow layer in said downstream flow region to further afford flame stabilization; and flowing gaseous fuel into said flow duct from said gaseous fuel nozzle for combining with the liquid fuel/air flow through said flow duct to obtain a lean pre-mixed fuel flow for reduced emissions.
Claim 9
Dependent Claim
258 words
In a dual-fuel pre-mixing burner assembly for a turbine having a burner assembly body, a liquid fuel nozzle disposed substantially centrally of and adjacent an inlet to said body, a flow duct carried by said body, said duct including an upstream converging section, a throat section and a downstream diverging section, inner and outer generally concentric passages adjacent said body inlet, and at least one gaseous fuel nozzle carried by said body, a method of combustion comprising the steps of: flowing fuel from said liquid fuel injection nozzle into said flow duct for flow in a generally downstream direction; introducing air through said inner passage into said flow duct having flow components in a first generally tangential direction and said generally downstream direction for mixing in said flow duct with said liquid fuel and affording a swirl to the flow exhausting from said diverging section; establishing downstream of said burner body a recirculation zone resultant from expanding the swirling exhaust flow from the diverging section of the flow duct to afford flame stabilization; flowing air through said outer passage bypassing said flow duct into a flow region downstream of said burner body with a flow component in a second generally tangential direction opposite said first tangential direction to establish therewith a shear flow layer in said downstream flow region to further afford flame stabilization; and flowing gaseous fuel into said flow duct from said gaseous fuel nozzle for combining with the liquid fuel/air flow through said flow duct to obtain a lean pre-mixed fuel flow for reduced emissions.
Claim 10
Dependent Claim
346 words
A pre-mixing burner assembly for a turbine, comprising: a burner assembly body having an inlet for flowing fuel and air in a generally downstream direction and having a fuel nozzle disposed substantially centrally of and adjacent said inlet to said body for supplying fuel for flow in the generally downstream direction; a flow duct, carried by said body and having an upstream converging section, a throat section and a downstream diverging section, for receiving fuel from said central nozzle and air from said inlet; inner and outer generally concentric passages adjacent said body inlet for flowing air through said body; at least one gaseous fuel nozzle carried by said body and located to flow gaseous fuel through said duct in the generally downstream direction; said inner passage lying in communication with said flow duct to supply air thereto for pre-mixing, in said duct, air and fuel to form a lean air and fuel mixture from said at least one of said central liquid fuel nozzle and said gaseous fuel nozzle and for delivery of said pre-mixed air and fuel to a flow region downstream of said duct; an inner swirler in said inner passage for delivering to said duct air having a flow component in a first tangential direction such that the pre-mixed fuel and air delivered from said duct to said flow region has a flow component in said first tangential direction; said converging section of said duct and said pre-mixed fuel and air, exiting said converging section of said duct, comprising a means for establishing a centerline recirculation zone in said flow region therefore affording flame stabilization; and an outer swirler means in said outer passage for delivering to said flow region downstream of said duct air having a flow component in a second tangential direction generally opposite to said first tangential direction and for establishing, in combination with the flow having said first tangential component, a generally annular shear layer in said flow region, said centerline recirculation zone and said annular shear layer comprising a means for flame stabilization in said burner assembly.
Claim 11
Dependent Claim
346 words
A pre-mixing burner assembly for a turbine, comprising: a burner assembly body having an inlet for flowing fuel and air in a generally downstream direction and having a fuel nozzle disposed substantially centrally of and adjacent said inlet to said body for supplying fuel for flow in the generally downstream direction; a flow duct, carried by said body and having an upstream converging section, a throat section and a downstream diverging section, for receiving fuel from said central nozzle and air from said inlet; inner and outer generally concentric passages adjacent said body inlet for flowing air through said body; at least one gaseous fuel nozzle carried by said body and located to flow gaseous fuel through said duct in the generally downstream direction; said inner passage lying in communication with said flow duct to supply air thereto for pre-mixing, in said duct, air and fuel to form a lean air and fuel mixture from said at least one of said central liquid fuel nozzle and said gaseous fuel nozzle and for delivery of said pre-mixed air and fuel to a flow region downstream of said duct; an inner swirler in said inner passage for delivering to said duct air having a flow component in a first tangential direction such that the pre-mixed fuel and air delivered from said duct to said flow region has a flow component in said first tangential direction; said converging section of said duct and said pre-mixed fuel and air, exiting said converging section of said duct, comprising a means for establishing a centerline recirculation zone in said flow region therefore affording flame stabilization; and an outer swirler means in said outer passage for delivering to said flow region downstream of said duct air having a flow component in a second tangential direction generally opposite to said first tangential direction and for establishing, in combination with the flow having said first tangential component, a generally annular shear layer in said flow region, said centerline recirculation zone and said annular shear layer comprising a means for flame stabilization in said burner assembly.
References Cited (Backward Citations)
US3605405A
Cited
US3853273A
Cited
US4222243A
Cited
US4194358A
Cited
US4982570A
Cited
US5165241A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1997-09-12 | 1998-03-14 | 1998-09-13 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 2001-09-12 | 2002-03-14 | 2002-09-13 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2005-09-12 | 2006-03-14 | 2006-09-13 | $7700.00 | Window Closed / Lapsed |