Patent US5675971A successfully refreshed from Google Patents.
US5675971A
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Dual fuel mixer for gas turbine combustor
Assignee: General Electric Co
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Filing: 1996-01-02
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Granted: 1997-10-14
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Expires: 2016-01-02
Abstract
Abstract An air fuel mixer is disclosed having a mixing duct, a shroud surrounding the upstream end of the mixing duct in which a fuel manifold is provided in flow communication with a fuel supply and control means, a set of inner and outer counter-rotating swirlers adjacent the upstream end of the mixing duct for imparting swirl to an air stream, a hub separating the inner and outer annular swirlers to allow independent rotation of the air stream, and a centerbody located axially along and substantially the full length of the mixing duct. In order to inject one type of fuel into the mixing duct, fuel is supplied to the outer annular swirlers which include hollow vanes with internal cavities, wherein the internal cavities of the outer swirler vanes are in fluid communication with the fuel manifold in the shroud. The outer swirler vanes further include a plurality of fuel passages therethrough in flow communication with the internal cavities. A second fuel can be injected into the mixing duct by means of a plurality of orifices in the centerbody wall which are in flow communication with a fuel supply and control means. In this way, high pressure air from a compressor is injected into the mixing duct through the swirlers to form an intense shear region and fuel is injected into the mixing duct from the outer swirler vane passages and/or the centerbody orifices so that the high pressure air and the fuel is uniformly mixed therein so as to produce minimal formation of pollutants when a fuel/air mixture is exhausted out the downstream end of the mixing duct into the combustor and ignited.
Inventors
- 👤 Paul R. Angel
- 👤 James M. Caldwell
- 👤 Paul V. Heberling
- 👤 Anthony J. Dean
- 👤 Narendra D. Joshi
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-24 13:21
CPC Classifications
F; F23; F23R; F23R3/00; F23R3/28; F23R3/286; F23D; F23D2900/00; F23D2900/14; F23D2900/14004
Claims Analysis
Total Claims: 11
Claim 1
Independent Claim
364 words
An apparatus for premixing fuel and air prior to combustion in a gas turbine engine, comprising; (a) a linear mixing duct having a circular cross section defined by a wall; (b) a shroud surrounding the upstream end of said mixing duct, said shroud having contained therein a fuel manifold in flow communication with a fuel supply and control means; (c) a set of inner and outer annular counter-rotating swirlers adjacent the upstream end of said mixing duct for imparting swirl to an air stream, said outer annular swirlers including hollow vanes with internal cavities, wherein the internal cavities of said outer swirler vanes are in fluid communication with said fuel manifold, said outer swirler vanes further including a plurality of fuel passages therethrough in flow communication with said internal cavities to inject fuel into said mixing duct; (d) a hub separating said inner and outer annular swirlers to allow independent rotation of said air stream; and (e) a centerbody defined by a circular wall located axially along and substantially the full length of said mixing duct, said centerbody further comprising: (1) a plurality of orifices in said wall in flow communication with a a fuel supply and control means, wherein said orifices are located immediately downstream of said inner and outer annular swirlers to inject fuel into said mixing duct; (2) a main air passage in flow communication with an air supply; and (3) an air passage surrounding each of said fuel orifices, said air passages being in flow communication with said main air passage, wherein air from said air passages assists atomization of fuel injected through said orifices and directs fuel away from an outer annular surface of said centerbody; wherein high pressure air from a compressor is injected into said mixing duct through said swirlers to form an intense shear region and fuel is injected into said duct from at least one of said centerbody orifices and said outer swirler vane passages so that the high pressure air and the fuel is uniformly mixed therein so as to produce minimal formation of pollutants when the fuel/air mixture is exhausted out the downstream end of said mixing duct into the combustor and ignited.
Claim 2
Independent Claim
364 words
An apparatus for premixing fuel and air prior to combustion in a gas turbine engine, comprising; (a) a linear mixing duct having a circular cross section defined by a wall; (b) a shroud surrounding the upstream end of said mixing duct, said shroud having contained therein a fuel manifold in flow communication with a fuel supply and control means; (c) a set of inner and outer annular counter-rotating swirlers adjacent the upstream end of said mixing duct for imparting swirl to an air stream, said outer annular swirlers including hollow vanes with internal cavities, wherein the internal cavities of said outer swirler vanes are in fluid communication with said fuel manifold, said outer swirler vanes further including a plurality of fuel passages therethrough in flow communication with said internal cavities to inject fuel into said mixing duct; (d) a hub separating said inner and outer annular swirlers to allow independent rotation of said air stream; and (e) a centerbody defined by a circular wall located axially along and substantially the full length of said mixing duct, said centerbody further comprising: (1) a plurality of orifices in said wall in flow communication with a a fuel supply and control means, wherein said orifices are located immediately downstream of said inner and outer annular swirlers to inject fuel into said mixing duct; (2) a main air passage in flow communication with an air supply; and (3) an air passage surrounding each of said fuel orifices, said air passages being in flow communication with said main air passage, wherein air from said air passages assists atomization of fuel injected through said orifices and directs fuel away from an outer annular surface of said centerbody; wherein high pressure air from a compressor is injected into said mixing duct through said swirlers to form an intense shear region and fuel is injected into said duct from at least one of said centerbody orifices and said outer swirler vane passages so that the high pressure air and the fuel is uniformly mixed therein so as to produce minimal formation of pollutants when the fuel/air mixture is exhausted out the downstream end of said mixing duct into the combustor and ignited.
Claim 3
Dependent Claim
37 words
The apparatus of claim 1, wherein gaseous fuel is injected into said mixing duct by means of said outer swirler vane passages and liquid fuel is injected into said mixing duct by means of said centerbody orifices.
Claim 4
Dependent Claim
23 words
The apparatus of claim 1, wherein said mixing duct converges substantially uniformly as it extends from its upstream end to its downstream end.
Claim 5
Dependent Claim
22 words
The apparatus of claim 1, wherein said centerbody converges substantially uniformly as it extends from its upstream end to its downstream end.
Claim 6
Independent Claim
335 words
An apparatus for premixing fuel and air prior to combustion in a gas turbine engine, comprising: (a) a linear mixing duct having a circular cross section defined by a wall; (b) a shroud surrounding the upstream end of said mixing duct, said shroud having contained therein a fuel manifold in flow communication with a fuel supply and control means; (c) a set of inner and outer annular counter-rotating swirlers adjacent the upstream end of said mixing duct for imparting swirl to an air stream, said outer annular swirlers including hollow vanes with internal cavities, wherein the internal cavities of said outer swirler vanes are in fluid communication with said fuel manifold, said outer swirler vanes further including a plurality of fuel passages therethrough in flow communication with said internal cavities to inject fuel into said mixing duct; (d) a hub separating said inner and outer annular swirlers to allow independent rotation of said air stream; (e) a centerbody defined by a circular wall located axially along and substantially the full length of said mixing duct, said centerbody wall having a plurality of orifices therein in flow communication with a fuel supply and control means, wherein said orifices are located immediately downstream of said inner and outer annular swirlers to inject fuel into said mixing duct; and (f) means for supplying purge air to said fuel manifold in said shroud and said fuel passages in said outer swirler vanes when fuel is being injected into said mixing duct from said centerbody orifices; wherein high pressure air from a compressor is injected into said mixing duct through said swirlers to form all intense shear region and fuel is injected into said mixing duct from at least one of said centerbody orifices and said outer swirler vane passages so that the high pressure air and the fuel is uniformly mixed therein so as to produce minimal formation of pollutants when the fuel/air mixture is exhausted out the downstream end of said mixing duct into the combustor and ignited.
Claim 7
Independent Claim
335 words
An apparatus for premixing fuel and air prior to combustion in a gas turbine engine, comprising: (a) a linear mixing duct having a circular cross section defined by a wall; (b) a shroud surrounding the upstream end of said mixing duct, said shroud having contained therein a fuel manifold in flow communication with a fuel supply and control means; (c) a set of inner and outer annular counter-rotating swirlers adjacent the upstream end of said mixing duct for imparting swirl to an air stream, said outer annular swirlers including hollow vanes with internal cavities, wherein the internal cavities of said outer swirler vanes are in fluid communication with said fuel manifold, said outer swirler vanes further including a plurality of fuel passages therethrough in flow communication with said internal cavities to inject fuel into said mixing duct; (d) a hub separating said inner and outer annular swirlers to allow independent rotation of said air stream; (e) a centerbody defined by a circular wall located axially along and substantially the full length of said mixing duct, said centerbody wall having a plurality of orifices therein in flow communication with a fuel supply and control means, wherein said orifices are located immediately downstream of said inner and outer annular swirlers to inject fuel into said mixing duct; and (f) means for supplying purge air to said fuel manifold in said shroud and said fuel passages in said outer swirler vanes when fuel is being injected into said mixing duct from said centerbody orifices; wherein high pressure air from a compressor is injected into said mixing duct through said swirlers to form all intense shear region and fuel is injected into said mixing duct from at least one of said centerbody orifices and said outer swirler vane passages so that the high pressure air and the fuel is uniformly mixed therein so as to produce minimal formation of pollutants when the fuel/air mixture is exhausted out the downstream end of said mixing duct into the combustor and ignited.
Claim 8
Independent Claim
151 words
An apparatus for premixing fuel and air prior to combustion in a gas turbine engine, comprising: (a) a linear mixing duct having a circular cross section defined by a wall; (b) means for mixing fuel and air in said mixing duct; (c) a centerbody located along a central axis of said mixing duct and extending substantially the full length of said mixing duct, said centerbody further comprising: (1) a plurality of orifices therein to inject fuel into said mixing duct; (2) a main air passage in flow communication with an air supply; and (3) at least one air passage located adjacent each of said fuel orifices, said air passages being in flow communication with said main air passage, wherein air from said air passages directs fuel away from an outer annular surface of said centerbody and assists atomization of said fuel; and (d) means for supplying fuel to said centerbody orifices.
Claim 9
Independent Claim
151 words
An apparatus for premixing fuel and air prior to combustion in a gas turbine engine, comprising: (a) a linear mixing duct having a circular cross section defined by a wall; (b) means for mixing fuel and air in said mixing duct; (c) a centerbody located along a central axis of said mixing duct and extending substantially the full length of said mixing duct, said centerbody further comprising: (1) a plurality of orifices therein to inject fuel into said mixing duct; (2) a main air passage in flow communication with an air supply; and (3) at least one air passage located adjacent each of said fuel orifices, said air passages being in flow communication with said main air passage, wherein air from said air passages directs fuel away from an outer annular surface of said centerbody and assists atomization of said fuel; and (d) means for supplying fuel to said centerbody orifices.
Claim 10
Dependent Claim
129 words
The apparatus of claim 6, said fuel/air mixing means further comprising: (a) a set of inner and outer annular counter-rotating swirlers adjacent the upstream end of said mixing duct for imparting swirl to an air stream; and (b) a hub separating said inner and outer annular swirlers to allow independent rotation of said air stream; wherein high pressure air from a compressor is injected into said mixing duct through said swirlers to form an intense shear region and fuel is injected into said mixing duct from said centerbody orifices so that the high pressure air and the fuel is uniformly mixed therein so as to produce minimal formation of pollutants when the fuel/air mixture is exhausted out the downstream end of said mixing duct into the combustor and ignited.
Claim 11
Dependent Claim
17 words
The apparatus of claim 6, wherein said air passages are concentric with and encircle said fuel orifices.
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) | 2000-10-13 | 2001-04-14 | 2001-10-14 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 2004-10-13 | 2005-04-14 | 2005-10-14 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2008-10-13 | 2009-04-14 | 2009-10-14 | $7700.00 | Window Closed / Lapsed |