US5680766A
Expired / Lapsed
US
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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: 1997-10-28
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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
- 👤 Narendra D. Joshi
- 👤 Paul R. Angel
- 👤 James M. Caldwell
- 👤 Paul V. Heberling
- 👤 Anthony J. Dean
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-04 18:55
CPC Classifications
F; F23; F23R; F23R3/00; F23R3/28; F23R3/36; F23C; F23C7/00; F23C7/002; F23C7/004; F23D; F23D17/00; F23D17/002; F23R3/02; F23R3/04; F23R3/10; F23R3/12; F23R3/14; F23C2900/00; F23C2900/07001; F23D2209/00; F23D2209/30
Claims Analysis
Total Claims: 22
Claim 1
Independent Claim
279 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 set of inner and outer annular counter-rotating swirlers adjacent the upstream end of said mixing duct; (c) a hub separating said inner and outer annular swirlers to allow independent rotation of an air stream through said swirlers; (d) 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 main fuel passage; (2) a plurality of fuel ducts located immediately downstream of said inner and outer annular swirlers in flow communication with said main fuel passage, said fuel ducts being oriented substantially radially outward and being positioned at designated locations circumferentially around said centerbody; and (3) at least two openings located immediately at the outer radial ends of said fuel ducts, wherein said openings are straight passages oriented with respect to each other so that fuel jets injected into said mixing duct therefrom impinge on each other to enhance atomization of the fuel in the mixing duct; and (d) a fuel supply in flow communication with said centerbody main fuel passage; 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 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
279 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 set of inner and outer annular counter-rotating swirlers adjacent the upstream end of said mixing duct; (c) a hub separating said inner and outer annular swirlers to allow independent rotation of an air stream through said swirlers; (d) 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 main fuel passage; (2) a plurality of fuel ducts located immediately downstream of said inner and outer annular swirlers in flow communication with said main fuel passage, said fuel ducts being oriented substantially radially outward and being positioned at designated locations circumferentially around said centerbody; and (3) at least two openings located immediately at the outer radial ends of said fuel ducts, wherein said openings are straight passages oriented with respect to each other so that fuel jets injected into said mixing duct therefrom impinge on each other to enhance atomization of the fuel in the mixing duct; and (d) a fuel supply in flow communication with said centerbody main fuel passage; 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 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
26 words
The apparatus of claim 1, wherein said openings are angled with respect to an axis through said fuel duct in a range of +5° to -5°.
Claim 4
Dependent Claim
26 words
The apparatus of claim 1, wherein a fan spray is formed by the impingement of said fuel jets injected into said mixing duct through said openings.
Claim 5
Dependent Claim
12 words
The apparatus of claim 3, wherein said fan spray is substantially planar.
Claim 6
Dependent Claim
20 words
The apparatus of claim 4, wherein said fan spray is oriented substantially perpendicular to said air swirled by said swirlers.
Claim 7
Dependent Claim
20 words
The apparatus of claim 4, wherein said fan spray is oriented substantially parallel to said air swirled by said swirlers.
Claim 8
Dependent Claim
22 words
The apparatus of claim 4, wherein said fan spray is oriented at a designated angle to said air swirled by said swirlers.
Claim 9
Dependent Claim
17 words
The apparatus of claim 1, wherein said fuel duct openings lie in more than one axial plane.
Claim 10
Dependent Claim
68 words
The apparatus of claim 1, said centerbody further comprising: (a) a main air passage in flow communication with an air supply; and (b) at least one air passage located adjacent each fuel duct, 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.
Claim 11
Independent Claim
251 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 set of inner and outer annular counter-rotating swirlers adjacent the upstream end of said mixing duct; (c) a hub separating said inner and outer annular swirlers to allow independent rotation of an air stream through said swirlers; (d) 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 main fuel passage; and (2) a plurality of angled fuel passages in flow communication with said main fuel passage, each of said angled fuel passages being oriented substantially radially outward from a centerline axis of said apparatus and with respect to an adjacent angled fuel passage so that fuel jets injected into said mixing duct therefrom impinge on each other to enhance atomization of the fuel in the mixing duct; and (e) a fuel supply in flow communication with said centerbody main fuel passage; 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 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 12
Independent Claim
251 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 set of inner and outer annular counter-rotating swirlers adjacent the upstream end of said mixing duct; (c) a hub separating said inner and outer annular swirlers to allow independent rotation of an air stream through said swirlers; (d) 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 main fuel passage; and (2) a plurality of angled fuel passages in flow communication with said main fuel passage, each of said angled fuel passages being oriented substantially radially outward from a centerline axis of said apparatus and with respect to an adjacent angled fuel passage so that fuel jets injected into said mixing duct therefrom impinge on each other to enhance atomization of the fuel in the mixing duct; and (e) a fuel supply in flow communication with said centerbody main fuel passage; 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 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 13
Dependent Claim
25 words
The apparatus of claim 10, wherein said angled fuel passages are angled with respect to a radial axis in a range of +5° to -5°.
Claim 14
Dependent Claim
17 words
The apparatus of claim 10, wherein said angled fuel passages lie in more than one axial plane.
Claim 15
Independent Claim
287 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 set of inner and outer annular counter-rotating swirlers adjacent the upstream end of said mixing duct for imparting swirl to an air stream; (c) a hub separating said inner and outer annular swirlers to allow independent rotation of said air stream; (d) means for injecting a plurality of fuel jets into an upstream end of said mixing duct wherein said fuel jets are injected substantially perpendicular to an air stream in said mixing duct and oriented so that each one impinges with at least one adjacent fuel jet to enhance atomization of said fuel, said fuel injection means further comprising: (1) 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; and (2) said outer annular swirler including hollow vanes with internal cavities, wherein the internal cavities of said outer swirler vanes are in flow communication with said fuel manifold, and said outer swirler vanes have a plurality of passages therethrough in flow communication with said internal cavities to inject said fuel jets into said mixing duct; 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 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 16
Independent Claim
287 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 set of inner and outer annular counter-rotating swirlers adjacent the upstream end of said mixing duct for imparting swirl to an air stream; (c) a hub separating said inner and outer annular swirlers to allow independent rotation of said air stream; (d) means for injecting a plurality of fuel jets into an upstream end of said mixing duct wherein said fuel jets are injected substantially perpendicular to an air stream in said mixing duct and oriented so that each one impinges with at least one adjacent fuel jet to enhance atomization of said fuel, said fuel injection means further comprising: (1) 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; and (2) said outer annular swirler including hollow vanes with internal cavities, wherein the internal cavities of said outer swirler vanes are in flow communication with said fuel manifold, and said outer swirler vanes have a plurality of passages therethrough in flow communication with said internal cavities to inject said fuel jets into said mixing duct; 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 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 17
Independent Claim
296 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 set of inner and outer annular counter-rotating swirlers adjacent the upstream end of said mixing duct for imparting swirl to an air stream; (c) a hub separating said inner and outer annular swirlers to allow independent rotation of said air stream; (d) means for injecting a plurality of fuel jets into an upstream end of said mixing duct, wherein said fuel jets are injected substantially perpendicular to an air stream in said mixing duct and oriented so that each one impinges with at least one adjacent fuel jet to enhance atomization of said fuel, said fuel injection means further comprising: (1) 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; (2) said outer annular swirler including hollow vanes with internal cavities, wherein the internal cavities of said outer swirler vanes are in flow communication with said fuel manifold; and (3) said hub having a circumferential slot in fluid communication with said outer swirler vane internal cavities and a plurality of passages extending downstream from said slot to inject said fuel jets into said mixing duct; 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 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 18
Independent Claim
296 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 set of inner and outer annular counter-rotating swirlers adjacent the upstream end of said mixing duct for imparting swirl to an air stream; (c) a hub separating said inner and outer annular swirlers to allow independent rotation of said air stream; (d) means for injecting a plurality of fuel jets into an upstream end of said mixing duct, wherein said fuel jets are injected substantially perpendicular to an air stream in said mixing duct and oriented so that each one impinges with at least one adjacent fuel jet to enhance atomization of said fuel, said fuel injection means further comprising: (1) 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; (2) said outer annular swirler including hollow vanes with internal cavities, wherein the internal cavities of said outer swirler vanes are in flow communication with said fuel manifold; and (3) said hub having a circumferential slot in fluid communication with said outer swirler vane internal cavities and a plurality of passages extending downstream from said slot to inject said fuel jets into said mixing duct; 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 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 19
Independent Claim
251 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 set of inner and outer annular counter-rotating swirlers adjacent the upstream end of said mixing duct for imparting swirl to an air stream; (c) a hub separating said inner and outer annular swirlers to allow independent rotation of said air stream; (d) means for injecting a plurality of fuel jets into an upstream end of said mixing duct, wherein said fuel jets are injected substantially parallel to an air stream in said mixing duct and oriented so that each one impinges with at least one adjacent fuel jet to enhance atomization of said fuel, said fuel injection means further comprising: (1) a centerbody located along a central axis of said mixing duct and extending substantially the full length of said mixing duct, said centerbody including a plurality of orifices therein to inject said fuel jets into said mixing duct; and (2) means for supplying fuel to said centerbody orifices; 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 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 20
Independent Claim
251 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 set of inner and outer annular counter-rotating swirlers adjacent the upstream end of said mixing duct for imparting swirl to an air stream; (c) a hub separating said inner and outer annular swirlers to allow independent rotation of said air stream; (d) means for injecting a plurality of fuel jets into an upstream end of said mixing duct, wherein said fuel jets are injected substantially parallel to an air stream in said mixing duct and oriented so that each one impinges with at least one adjacent fuel jet to enhance atomization of said fuel, said fuel injection means further comprising: (1) a centerbody located along a central axis of said mixing duct and extending substantially the full length of said mixing duct, said centerbody including a plurality of orifices therein to inject said fuel jets into said mixing duct; and (2) means for supplying fuel to said centerbody orifices; 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 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 21
Independent Claim
289 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 set of inner and outer annular counter-rotating swirlers adjacent the upstream end of said mixing duct; (c) a hub separating said inner and outer annular swirlers to allow independent rotation of an air stream through said swirlers; (d) 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 located immediately downstream of said inner and outer swirlers to inject fuel into said mixing duct, each of said orifices being oriented with respect to at least one adjacent orifice such that fuel jets injected into said mixing duct therefrom impinge on each other; (2) a main air passage in flow communication with an air supply; and (3) at least one air passage located adjacent each pair of said adjacent 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 (e) a fuel supply in flow communication with said orifices; 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 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 22
Independent Claim
289 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 set of inner and outer annular counter-rotating swirlers adjacent the upstream end of said mixing duct; (c) a hub separating said inner and outer annular swirlers to allow independent rotation of an air stream through said swirlers; (d) 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 located immediately downstream of said inner and outer swirlers to inject fuel into said mixing duct, each of said orifices being oriented with respect to at least one adjacent orifice such that fuel jets injected into said mixing duct therefrom impinge on each other; (2) a main air passage in flow communication with an air supply; and (3) at least one air passage located adjacent each pair of said adjacent 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 (e) a fuel supply in flow communication with said orifices; 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 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.
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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) | 2000-10-27 | 2001-04-28 | 2001-10-28 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 2004-10-27 | 2005-04-28 | 2005-10-28 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2008-10-27 | 2009-04-28 | 2009-10-28 | $7700.00 | Window Closed / Lapsed |