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WO2018144008A1 - Chambre de combustion avec pré-mélangeur en treillis tridimensionnel - Google Patents

Chambre de combustion avec pré-mélangeur en treillis tridimensionnel Download PDF

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Publication number
WO2018144008A1
WO2018144008A1 PCT/US2017/016420 US2017016420W WO2018144008A1 WO 2018144008 A1 WO2018144008 A1 WO 2018144008A1 US 2017016420 W US2017016420 W US 2017016420W WO 2018144008 A1 WO2018144008 A1 WO 2018144008A1
Authority
WO
WIPO (PCT)
Prior art keywords
fuel
air
premixer
combustion chamber
fluid communication
Prior art date
Application number
PCT/US2017/016420
Other languages
English (en)
Inventor
Gilles Bourque
Original Assignee
Siemens Aktiengesellschaft
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Priority to PCT/US2017/016420 priority Critical patent/WO2018144008A1/fr
Priority to PCT/US2017/044827 priority patent/WO2018144065A1/fr
Priority to PCT/US2017/044792 priority patent/WO2018144064A1/fr
Priority to PCT/US2018/021102 priority patent/WO2019027508A1/fr
Publication of WO2018144008A1 publication Critical patent/WO2018144008A1/fr

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/005—Combined with pressure or heat exchangers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/002—Wall structures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03044—Impingement cooled combustion chamber walls or subassemblies
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03342—Arrangement of silo-type combustion chambers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03343—Pilot burners operating in premixed mode

Definitions

  • the invention relates to combustors for combustion or gas turbine engines. More particularly, the invention relates to combustors of combustion or gas turbine engines, which incorporate fuel-air premixers having a monolithic, three-dimensional lattice structure of selectively oriented, asymmetrical- and serpentine-shaped metallic webs and premixer passages formed therein.
  • Emission level requirements established for industrial combustion or gas turbine engines, limit the quantity of oxide of nitrogen (NOx) produced during engine operation.
  • a known way to reduce emissions of nitrogen oxides is to reduce the combustion reaction temperature, and this requires premixing of the fuel and a large proportion, preferably all, of the combustion air before combustion occurs.
  • the oxides of nitrogen (NOx) are commonly reduced by use of multi-stage fuel injection. In multi-staged combustion, all the stages of combustion seek to provide lean combustion and hence the low combustion temperatures required to minimize NOx.
  • the term "lean combustion” means combustion of fuel in air where the fuel to air ratio (“FAR”) is low, i.e. less than the stoichiometric ratio.
  • the premixer has a fuel and air mixing duct, which mixes the fuel and air at a desired fuel-air ratio and transfers the mixture, via a fuel and air discharge duct, into a combustion zone of the combustion chamber.
  • a secondary fuel and air mixing duct supplies a mixture of fuel and air into a secondary combustion zone, via a secondary fuel and air discharge duct.
  • Some combustors incorporate a tertiary fuel and air mixing duct, a tertiary fuel and air discharge duct, and a tertiary combustion zone.
  • One problem associated with gas turbine engines is caused by pressure and flow rate temporal fluctuations in either one or both of the compressed air source feeding the combustor premixer, or combustion gas generated within the combustion chamber and flowing down stream into the turbine section of the engine.
  • Pressure fluctuations in the compressed air supply and/or combustion gas flow through the engine locally disrupt at different times the fuel-air ratio, which adversely influences engine emissions.
  • a pressure fluctuation in the air intake plenum propagates through the air duct and disrupts the mixture ratio within the fuel and air mixing duct.
  • pressure fluctuations in the combustion gas within the combustion chamber may propagate upstream, via the fuel and air discharge duct, and produce fluctuations in the fuel-air ratio at the exit of the fuel and air mixing ducts.
  • the fuel-air ratio in both the premixer' s fuel and air mixing ducts and the combustion chamber are disrupted by the combustion gas-pressure fluctuation.
  • frequency fluctuations in the compressed air supplied by the compressor coincides or couples with frequency fluctuations in the combustion gas.
  • Such coupling effectively disrupts fuel-air ratio stability within the fuel and air mixing ducts, from both the inlet and exhaust portions of those ducts.
  • Extreme, temporal pressure and flow fluctuations, whether coupled or uncoupled, may lead to severe damage, or failure, of components if the frequency of the pressure fluctuations coincides with the natural frequency of a vibration mode of one or more of the components.
  • an industrial gas turbine engine 20 shown in FIG. 1, comprises in axial flow series an inlet 22, a compressor section 24, a combustion section 26 (also sometimes referred to as a combustion chamber assembly), a turbine section 28, a power turbine section 30 and an exhaust 32.
  • the turbine section 28 is arranged to drive the compressor section 24 via one or more shafts (not shown).
  • the power turbine section 30 is arranged to drive an electrical generator 36 via a shaft 34.
  • the combustion section 26 comprises a plurality of equally circumferentially spaced combustors 38. Longitudinal axes of the combustors 38 are arranged to extend in generally radial directions. The inlets of the combustors 38 are at their radially outermost ends and their outlets are at their radially innermost ends.
  • the casing of the combustion section 26 incorporates an air intake plenum, which is in communication with the compressor section compressed air output, for providing compressed air to the inlets of the combustors 38.
  • Combustion gas generated within the combustor 38 flows through a corresponding transition 39, and thereafter into the turbine section 28.
  • Known combustor designs include, without limitation, so-called can, annular, and can-annular designs.
  • the combustor 40 includes a combustor outer casing 42, which receives compressed air CP from the compressor section via an air intake 44.
  • An annular air intake plenum 46 is defined between the interior of the combustor outer casing 42 and a fuel-air premixer assembly (“premixer assembly”) 47.
  • the premixer assembly 47 receives compressed air and fuel from separate sources, combines the fuel and air into a fuel and air mixture, and discharges the fuel and air mixture into a combustion chamber of the combustor 40.
  • the air intake plenum 46 is in fluid communication, through air duct passages in the outer walls that form the premixer assembly 47, with respective, separate and isolated primary fuel and air mixing duct ("FAMD") 48, secondary FAMD 50, and tertiary FAMD 52, via respective upper 54 and lower 56 primary air ducts, secondary air duct 58 and tertiary air duct 62.
  • FMD primary fuel and air mixing duct
  • each of the air ducts 54, 56, 58 and 62, as well as each of the FAMDs 48, 50, and 52 is annular-shaped, arrayed about the full circumference of the premixer, with respect to a central axis of the combustor 40.
  • one or more of the aforementioned air ducts 54, 56, 58 and 62, and/or FAMDs 48, 50, and 52 comprise a plurality of equally circumferentially-spaced conduits or channels, analogous to spokes of a bicycle wheel.
  • one or more of the air ducts 54, 56, 58 and 62 are annular-shaped, while one or more of the FAMDs 48, 50, and 52 are separate conduits or channels, analogous to tentacles of an octopus.
  • a plurality of each of the respective air ducts 54, 56, 58, 62, and their corresponding FAMDs 48, 50 and 52 are unified conduit or channel structures that are equally arrayed about the circumference of the premixer assembly 47, analogous to spokes of a bicycle wheel.
  • the primary FAMD 48 is in fluid communication with an annular manifold of a primary fuel delivery system 70.
  • the secondary FAMD 50 is in fluid communication with an annular manifold of a secondary fuel delivery system 72
  • the tertiary FAMD 52 is in fluid communication with an annular manifold of a tertiary fuel delivery system 74.
  • fuel supplied by each corresponding fuel delivery system 70, 72, 74 is entrained within the compressed air supplied by the respective corresponding air ducts 54, 56, 58 and 62, at a desired fuel-air ratio.
  • the fuel and air mixture discharges from the primary FAMD 48 through primary fuel and air discharge duct 80 ("FADD").
  • FADD primary fuel and air discharge duct 80
  • a flow directing swirler 48D is incorporated on the downstream end of the FAMD 48, or any of the other FAMDs, in order to direct the fuel-air mixture FA1 within the corresponding primary fuel and air discharge duct 80.
  • the fuel and air mixture discharges from secondary FAMD 50 via secondary fuel and air discharge duct (“FADD") 82, and from the tertiary FAMD 52 via tertiary fuel and air discharge duct (“FADD”) 84. In this embodiment of FIGs.
  • each of the air ducts 54, 56, 58 and 62, each of the FAMDs 48, 50, and 52 and each of the FADDs 80, 82 and 84 is annular-shaped, arrayed about the full circumference of the premixer, with respect to a central axis of the combustor 40.
  • FAMDs 48, 50, and 52, and/or FADDs 80, 82 and 84 comprise a plurality of equally circumferentially-spaced conduits or channels, analogous to spokes of a bicycle wheel.
  • one or more of the air ducts 54, 56, 58 and 62 are annular-shaped, while one or more of the FAMDs 48, 50, and 52 and/or FADDs 80, 82 and 84, are separate conduits or channels, analogous to tentacles of an octopus.
  • a plurality of each of the respective air ducts 54, 56, 58, and 62 corresponding adjoining FAMDs 48, 50 and 52, and corresponding adjoining FADDS 80, 82, and 84 are unified conduit or channel structures that are equally arrayed about the circumference of the premixer assembly 47, analogous to spokes of a bicycle wheel.
  • annular-shaped embodiments of air ducts 54, 56, 58 and 62 are only annular-shaped embodiments of air ducts 54, 56, 58 and 62,
  • the combustor 40 has a stepped combustion chamber 90, the upper axial end of which is defined by an upstream wall 91.
  • the upstream wall 91 defines an upstream axial limit of a primary combustion zone 92, and a primary annular wall 93 defines a circumferential axial limit of the primary combustion zone.
  • the fuel and air mixture supplied by the primary, annular FAMD 48 enters the primary combustion zone 92 via the corresponding primary fuel and air discharge duct 80 (or in other embodiments by separate conduit FADDs 80), as indicated by the arrow FA1.
  • the combustion chamber 90 has a secondary combustion zone 94, circumferentially defined by a secondary annular wall 95, downstream of the primary combustion zone 92.
  • the fuel and air mixture supplied by the secondary FAMD 50 enters the secondary combustion zone 94 via the corresponding secondary fuel and air discharge ducts 82 (arrow FA2).
  • a tertiary combustion zone 96 is circumferentially defined by a tertiary annular wall
  • radially aligned, circumferentially symmetrical, air slots are formed between respective FAMDs 48, 50, 52, and their corresponding air ducts 54, 56, 58, 62, in order to normalize temporal pressure fluctuations within the FAMDs.
  • the primary FAMD 48 forms a primary fuel air mixing chamber 48A.
  • Elongated, radially aligned and symmetrically oriented, upper primary air slots 48B, which are formed in the primary fuel air mixing chamber 48A, are in fluid communication with the upper primary air duct 54 (airflow arrow A).
  • elongated, radially aligned and symmetrically oriented, lower primary air slots 48C are in fluid communication with the lower primary air duct 56 (airflow arrow B).
  • each of the previously described the fuel and air mixing ducts (“FAMDs”) 48, 50, 52, their respective air ducts 54, 56, 58 and 62, and respective fuel and air discharge ducts (“FADDs”) 80, 82, 84 are symmetrically oriented about the circumference of the outer annular wall of the premixer assembly 47 and the symmetrical, annular intake plenum 46.
  • FAMDs 48, 50 and 52 airflow into FAMDs 48, 50 and 52 is not inherently uniform.
  • localized combustion gas flow rate and pressure varies radially and axially within the volume of the combustion chamber 90, which means that localized back pressure BP combustion gas flow, upstream into any of the respective primary FADD 80, secondary FADD 82, and tertiary FADD 84 is not necessarily uniform about the entire combustion chamber, even in the absence of temporal combustion fluctuations ⁇ .
  • Exemplary embodiments described herein locally vary structure of one or more of air ducts, fuel delivery passages, fuel and air mixing ducts, and/or fuel and air discharge ducts in the premixer of a combustor, in order to normalize fuel-air ratio at any location about the premixer' s three-dimensional volume, or in the combustion chamber, during steady-state operating conditions, and/or in order to stabilize fluctuations in compressed air supply to the premixer, and/or in order to stabilize fluctuations in combustion gas back pressure upstream into the premixer, and/or to stabilize mass flow and pressure fluctuations in combustion gas within the combustor' s combustion chamber.
  • the premixer is a monolithic, three-dimensional lattice structure of selectively oriented, asymmetrical- and serpentine-shaped metallic webs, for normalizing fuel-air ratio of a fuel and air mixture that is entrained throughout the volume of the premixer.
  • the web structure defines locally passages of varying profile and dimensions, which form: at least one air duct; and/or at least one fuel delivery passage, and/or at least one fuel and air mixing duct in fluid communication with the air ducts and the fuel delivery passage; and/or at least one fuel and air discharge duct, in fluid communication with the fuel and air mixing duct.
  • the premixer has a plurality of air ducts, and/or fuel delivery passages, and/or fuel and air mixing ducts, and/or fuel and air discharge ducts.
  • Cavity profiles of any one, or more, or all of the respective air ducts, fuel delivery passages, fuel and air mixing ducts, and fuel and air discharge ducts vary locally within the volume occupied by the premixer' s three-dimensional lattice structure, in order to normalize temporally, despite compressed air or combustion gas pressure fluctuations, more uniform fuel-air ratio mixture at any location about or within the premixer's internal volume.
  • local variation in the cavity profiles of any or all of the respective air ducts, fuel delivery passages, fuel and air mixing ducts, and fuel and air discharge ducts provide for selective local discharge of selectively varied fuel and air mixtures out of one or more of the fuel and air discharge ducts, in order to compensate for localized variations in the fuel-air ratio within the combustion chamber volume.
  • local variations in the premixer cavity profiles contributes to more uniform combustion gas mass flow within the combustion chamber volume of the combustor. Any of location, angular orientation, cross- sectional area, and profile of any compressed air inlet passage, air duct, FAMD,
  • FADD, and/or fuel/air mixture discharge passage within the premixer structure is selectively varied, in order to achieve more uniform fuel-air ratio within the combustor.
  • Some exemplary embodiments are utilized in premixers for combustors of combustion or gas turbine engines.
  • premixer embodiments locally vary structure of one or more of air ducts, fuel delivery passages, fuel and air mixing ducts, and/or fuel and air discharge ducts, in order to normalize fuel-air ratio at any location about the premixer's three-dimensional volume or in the combustion chamber, in response to any one or more of the following operational conditions: (a) during steady-state operation without temporal fluctuations in (i) compressed air supply to the premixer, or (ii) combustion gas back pressure upstream into the premixer, or (iii) combustion mass flow within the combustor; and/or (b) in order to stabilize fluctuations in compressed air supply to the premixer, and/or (c) in order to stabilize fluctuations in combustion gas back pressure upstream into the premixer; and/or (d) in order to stabilize combustion mass flow within the combustor.
  • the premixer is a monolithic, three-dimensional lattice structure of selectively oriented, asymmetrical- and serpentine-shaped metallic webs.
  • the web structure defines locally varying passages, which form: the aforementioned air ducts, fuel ducts, fuel delivery passages, fuel and air mixing ducts, and fuel and air discharge ducts.
  • the premixer, or a casting mold for the premixer is formed by additive manufacture. Additive manufacture processes facilitate formation of complex web and passages within the premixer that are not possible to manufacture by traditional solid metal fabrication, metal cutting, or metal casting methods.
  • Exemplary embodiments of the invention feature a combustor apparatus for a combustion turbine engine, which comprises a combustion chamber; an air intake plenum, for providing compressed air to the combustion chamber; a fuel delivery system, for delivering fuel to the combustion chamber; and a fuel-air premixer ("premixer").
  • the premixer has a monolithic, three- dimensional lattice structure of selectively oriented, asymmetrical- and serpentine- shaped metallic webs and premixer passages formed therein, for normalizing fuel-air ratio of a fuel and air mixture that is entrained throughout the volume of the premixer.
  • the premixer passages, in the monolithic, three-dimensional lattice structure form any one or more of: an air duct, in fluid communication with the air intake plenum; and/or a fuel delivery passage, in fluid communication with the fuel delivery system; and/or a fuel and air mixing duct, in fluid communication with the air duct and the fuel delivery passage; and/or a fuel and air discharge duct, in fluid communication with the fuel and air mixing duct and the combustion chamber.
  • a combustor apparatus for a combustion turbine engine comprising: an annular-shaped combustion chamber wall, defining a cylindrical-shaped combustion chamber, the combustion chamber wall having a combustion chamber axial centerline, and an upstream axial combustion chamber wall, defining an upstream axial end of the combustion chamber; a combustor outer casing, which envelops the combustion chamber; an air intake plenum, interposed between the combustor outer casing and the combustion chamber, for providing compressed air to the combustion chamber; a fuel delivery system, for delivering fuel to the combustion chamber; and an annular-shaped fuel-air premixer ("premixer”), which circumscribes the cylindrical-shaped combustion chamber in nested fashion.
  • premixer annular-shaped fuel-air premixer
  • the premixer has a premixer axial centerline, an inner annular wall proximate the combustion chamber and an outer annular wall in fluid communication with the air intake plenum.
  • the premixer has a monolithic, three-dimensional lattice structure of selectively oriented, asymmetrical- and serpentine-shaped metallic webs and premixer passages formed therein, for normalizing fuel-air ratio of a fuel and air mixture that is entrained throughout the volume of the premixer.
  • the premixer passages form any one or more of: a plurality of air ducts; and/or a fuel delivery passage; and/or a fuel and air mixing duct; and/or a fuel and air discharge duct.
  • the plurality of air ducts of the premixer are oriented asymmetrically about the outer annular wall thereof, in fluid communication with the air intake plenum, for selectively directing compressed air radially inwardly with respect to the premixer axial centerline, at selectively varying flow rates and pressures at different locations about the outer annular wall of the fuel-air premixer, for equalizing and stabilizing over time air fuel mixture within the fuel-air premixer.
  • the fuel delivery passage is in fluid communication with the fuel delivery system.
  • the fuel and air mixing duct is in fluid communication with the air ducts and the fuel delivery passage, and is oriented intermediate the inner and outer annular walls of the annular-shaped fuel-air premixer.
  • the fuel and air discharge duct is in fluid communication with the fuel and air mixing duct and the combustion chamber.
  • Additional exemplary embodiments of the invention feature a combustor apparatus for a combustion turbine engine, comprising an annular-shaped combustion chamber wall, defining a cylindrical-shaped combustion chamber.
  • the combustion chamber wall has a combustion chamber axial centerline, and an upstream axial, combustion chamber wall, defining an upstream axial end of the combustion chamber.
  • the combustor apparatus has an air intake plenum, for providing compressed air to the combustion chamber; a fuel delivery system, for delivering fuel to the combustion chamber; and an annular-shaped fuel-air premixer ("premixer").
  • the premixer has: an upper axial end; a lower axial end proximate the upstream axial wall of the combustion chamber; a premixer axial centerline, concentric with the axial centerline of the combustion chamber; an inner annular wall in fluid communication with the upstream axial wall of the combustion chamber; and an outer annular wall in fluid communication with the air intake plenum.
  • the premixer has a monolithic, three- dimensional lattice structure of selectively oriented, asymmetrical- and serpentine- shaped metallic webs and premixer passages formed therein.
  • the premixer passages form a first plurality of air ducts, oriented asymmetrically about the outer annular wall of the premixer, in fluid communication with the air intake plenum, for selectively directing compressed air radially inwardly with respect to the premixer axial centerline and axially toward the lower axial end thereof, at selectively varying flow rates and pressures at different locations about the outer annular wall of the fuel-air premixer, for equalizing and stabilizing over time air fuel mixture within the fuel-air premixer.
  • the premixer passages form a fuel delivery passage, in fluid communication with the fuel delivery system.
  • the premixer passages form a fuel and air mixing duct, in fluid communication with the first plurality of air ducts and the fuel delivery passage, with the fuel and air mixing duct oriented intermediate the inner and outer annular walls of the annular-shaped fuel-air premixer.
  • the premixer passages form a fuel and air discharge duct, in fluid communication with the fuel and air mixing duct and in fluid communication with the combustion through the lower axial end of the premixer.
  • FIG. 1 is a fragmentary, side elevational view of a known gas turbine engine
  • FIG. 2 is a fragmentary, axial cross-sectional view through a known, can-type combustion chamber
  • FIG. 3 is a cross- sectional view of part of the known primary fuel and air mixing duct (“FAMD”) shown in FIG. 2;
  • FIG. 4 is a cross-sectional view of an alternative embodiment of a known primary fuel and air mixing duct (“FAMD");
  • FIG. 5 is a fragmentary, axial cross-sectional view through an embodiment of a can-type combustion chamber, which is constructed in accordance with the present invention
  • FIG. 6 is a perspective view of another embodiment of a premixer that is constructed in accordance with an embodiment of the present invention, which has a monolithic, three-dimensional lattice structure of selectively oriented, asymmetrical - and serpentine-shaped metallic webs that define locally-varying passages;
  • FIG. 7 is a schematic, fragmentary cross-sectional view of a premixer that is constructed in accordance with another embodiment of the present invention.
  • FIG. 8 is a schematic, fragmentary cross-sectional view of a premixer that is constructed in accordance with another embodiment of the present invention.
  • FIG. 9 is a schematic, fragmentary cross-sectional view of a premixer that is constructed in accordance with another embodiment of the present invention.
  • FIG. 10 is a schematic, fragmentary cross-sectional view of a premixer that is constructed in accordance with another embodiment of the present invention.
  • FIG. 11 is an axial cross-sectional view through an embodiment of an annular- type combustion chamber of the present invention.
  • FIG. 12 is an axial cross-sectional view through another embodiment of an annular-type combustion chamber of the present invention .
  • FIG. 13 is a flowchart showing an embodiment of a method for normalizing fuel-air mixture within a combustor, by designing and manufacturing a premixer, in accordance with the present invention, which has a monolithic, three-dimensional lattice structure of selectively oriented, asymmetrical- and serpentine-shaped metallic webs that define locally varying passages.
  • identical reference numerals have been used, where possible, to designate identical elements that are common to the figures. The figures are not drawn to scale.
  • Exemplary embodiments of the invention are utilized in premixers for combustors of combustion or gas turbine engines.
  • Premixer embodiments described herein locally vary structure of one or more of air ducts, fuel delivery passages, fuel and air mixing ducts, and/or fuel and air discharge ducts, in order to normalize fuel-air ratio at any location about the premixer' s three-dimensional volume, or in the combustion chamber, during steady-state operating conditions, and/or in order to stabilize fluctuations in compressed air supply to the premixer, and/or in order to stabilize fluctuations in combustion gas back pressure upstream into the premixer, and/or in order to stabilize combustion mass flow within the combustor.
  • the premixer is a monolithic, three-dimensional lattice structure of selectively oriented, asymmetrical- and serpentine-shaped metallic webs.
  • the web structure defines locally varying passages, which form: the aforementioned air ducts, fuel ducts, fuel delivery passages, fuel and air mixing duct, and fuel and air discharge duct.
  • the premixer, or a casting mold for the premixer is formed by additive manufacture. Additive manufacture processes facilitate formation of complex web and passages within the premixer that are not possible to manufacture by traditional solid metal fabrication, metal cutting or metal casting methods.
  • FIG. 5 shows an exemplary embodiment of a three-stage, can-type combustor 100 for a combustion turbine engine, which incorporates features of the present invention.
  • the combustor 100 is substituted for the prior art combustor 38 of the combustion turbine engine 20, shown in FIG. 1 or the combustor 40 of FIGs. 2-4.
  • Features of the invention described herein are incorporated into other types of combustors, including annular and can-annular construction combustors, and other types of can combustors, for stationary power generation engines or aero-type engines.
  • the combustor 100 is a three-stage combustor, features of the invention described herein are incorporated into single-, two- or greater than three- stage combustors.
  • the combustor 100 is a can-type, three-stage combustor, enveloped by a combustor outer casing 102, which receives compressed air CP from the compressor of the engine section via an air intake 104.
  • An annular air intake plenum 106 is defined between the interior of the combustor outer casing 102 and a fuel-air premixer ("premixer") 150.
  • premixer 150 is a monolithic, three-dimensional lattice structure of selectively oriented, asymmetrical- and serpentine-shaped metallic webs. As shown in greater detail in the embodiment of FIG.
  • the premixer 150 has a generally annular shape, with an outer circumferential surface 152 that is in fluid communication with the air intake plenum 106, an inner circumferential surface 154 that abuts and is in fluid communication with a stepped, annular combustion chamber 120, an upper axial surface 156 that abuts the combustor outer casing 102, and a lower axial surface 158 that is in communication with the air intake 104 and the air intake plenum 106.
  • the metallic web forms a three-dimensional, lattice-like mesh 160 that defines locally apertures and passages 162 of varying profile and dimensions along one or more of its outer circumferential surface 152 (e.g., about the axial length L and about varying angular positions ⁇ along its outer circumferential surface), its inner circumferential surface 154, and optionally on its upper 156 and lower 158 axial surfaces, of the lattice structure of the premixer 150.
  • the lattice-like mesh 160 defines locally apertures and passages 162, within the interior volume of the premixer 150.
  • premixer 150 is shown as having an annular structure, in other embodiments, the premixer has different structural shapes, such as the hour glass-like external profile of the premixer 210 of FIG. 9. In other embodiments, the premixer has an asymmetrical structural profile.
  • the locally varying structure of the lattice-like mesh 160 with its integral passages 162 within the volume occupied by the premixer 150 form a plurality of locally varying profile, orientation, and dimension air ducts; fuel delivery passages; fuel and air mixing ducts ("FAMDs”), in fluid communication corresponding air ducts and the fuel delivery passages; and fuel and air discharge ducts (FADDs”), in fluid communication with their corresponding FAMDs.
  • the premixer has a single fuel delivery passage in communication with a fuel and air mixing duct, with the FAME) in communication with a corresponding fuel and air discharge duct.
  • the premixer is constructed with one or more of locally varying, annular- shaped air ducts, and/or fuel delivery passages, and/or FAMDs and/or FADDs. In other embodiments, the premixer is constructed with one or more of locally varying, channel- or conduit-like air ducts, and/or fuel delivery passages, and/or FAMDs and/or FADDs. In yet other embodiments, the premixer is constructed with one or more of locally varying combinations of annular-, channel- and/or conduit like air ducts, and/or fuel delivery passages, and/or FAMDs and/or FADDs.
  • profiles and/or spatial orientation of the various ducts and/or fuel passages is selectively altered locally within the lattice-like mesh 160 of the premixer 150, in order to achieve uniform fuel-air ratio within the premixed fuel and air mixture, throughout the premixer.
  • profiles and/or spatial orientation of the various ducts and/or fuel passages is selectively altered locally within the lattice-like mesh 160 of the premixer 150, in order to deliver uniform fuel and air mixture to the combustion chamber 120.
  • profiles and/or spatial orientation of the various ducts and/or fuel passages is selectively altered locally within the lattice-like mesh 160 of the premixer 150, in order to normalize mass flow of combustion gasses within the volume of the combustion chamber 120. Construction of the various ducts and fuel delivery passages is now described in detail.
  • the air intake plenum 106 is in fluid communication with the interior volume of the premixer 150, through passages 162 formed in the outer circumferential surface 152 and in some embodiments, the lower axial surface 158.
  • the passages 162 formed in outer circumferential surface 152 and/or the a lower axial surface 158 function as air duct passages (comparable to the air duct passages 54, 56, 58 and 62 of FIG.
  • FAMD primary fuel and air mixing duct
  • secondary FAMD 110 see exemplary airflow arrows C and D
  • tertiary FAMD 112 see exemplary airflow arrows E.
  • one or more of the FAMDs 108, 110 and 112 has an annular construction, fully circumscribing the combustion chamber 120.
  • one or more of the FAMDs 108, 110 and 112 comprises a plurality of circumferentially-spaced and arrayed discrete and separate conduits (with symmetrical, radially-oriented, angular spacing ⁇ , or alternatively, with asymmetrical angular spacing ⁇ or skewed or twisted, non-radial, spatial orientation).
  • the primary FAMD 108 is in fluid communication with an annular manifold of a primary fuel delivery system 114.
  • the secondary FAMD 110 is in fluid communication with an annular manifold of a secondary fuel delivery system 116
  • the tertiary FAMD 112 is in fluid communication with an annular manifold of a tertiary fuel delivery system 118.
  • fuel F supplied by each corresponding fuel delivery system 114, 116, 118 is entrained within the compressed air CP, at a desired fuel-air ratio.
  • the compressed air CP is supplied to the corresponding FAMDs 108, 110 and 112 through the respective corresponding air ducts that are formed within the passages 162, along the paths indicated by the flow arrows A, B, C, D and E.
  • one or more of the fuel delivery systems 114, 116 or 118 comprise pressurized fuel rails obtained from a pressurized fuel source, which in turn are coupled to fuel injection nozzles, orifices or the like that introduce fuel into its corresponding FAMD.
  • the fuel and air are mixed in each FAMD 108, 110, and 112.
  • the fuel and air mixture discharges from the primary FAMD 108 through primary fuel and air discharge duct ("FADD") 130 and primary FADD outlet 131.
  • FADD primary fuel and air discharge duct
  • a flow directing swirler is incorporated on the downstream end of the FAMD 108, or any of the other FAMDs 110 or 112, in order to direct the fuel-air mixture within the corresponding primary fuel and air discharge duct.
  • the fuel and air mixture discharges from secondary FAMD 110 via secondary fuel and air discharge duct 132, and from the tertiary FAMD 112 via tertiary fuel and air discharge duct 134.
  • one or more of the fuel and air discharge ducts 130, 132 or 134 has an annular construction, fully circumscribing the combustion chamber 120.
  • one or more of the fuel and air discharge ducts 130, 132 or 134 comprises a plurality of circumferentially- spaced and arrayed discrete and separate conduits (with symmetrical, radially-oriented, angular spacing ⁇ , similar to the FAMDs of the combustor 40 of FIG. 2, or alternatively, with asymmetrical angular spacing ⁇ or skewed or twisted, non-radial orientation).
  • one or more of the FADDs 130, and/or 132, and/or 134 have locally varying profiles, cross-sectional area, and orientation.
  • One or more of such FADDs have locally varying discharge orientation or outlet shape relative to the combustion chamber 120.
  • the respective fuel and air discharge ducts 130, 132, 134 are in fluid communication with, and discharge their respective fuel and air mixtures FA1, FA2 and FA3 into the combustion chamber 120.
  • discharge location of the FADDs 130, 132, 134 varies locally about the combustion chamber 120, for example to resist local variations in combustion back pressure BP, or backpressure pulsation ⁇ .
  • the combustion chamber 120 has an upper axial end that is defined by an upstream wall 121.
  • the upstream wall 121 defines an upstream axial limit of a primary combustion zone 122.
  • a primary annular wall 123 defines a circumferential axial limit of the primary combustion zone 122.
  • the fuel and air mixture supplied by the primary FAMDs 108 enters the primary combustion zone 122 via the corresponding, coupled array of primary fuel and air discharge ducts 130 (arrow FA1).
  • the combustion chamber 120 has a secondary combustion zone 124, circumferentially defined by a secondary annular wall 125, downstream of the primary combustion zone 122. The fuel and air mixture supplied by the secondary
  • FAMDs 110 enters the secondary combustion zone 124 via the corresponding, coupled array of secondary fuel and air discharge ducts 132 (arrow FA2).
  • a tertiary combustion zone 126 is circumferentially defined by a tertiary annular wall 127, downstream of the secondary combustion zone 124.
  • the fuel and air mixture supplied by the tertiary FAMDs 112 enters the tertiary combustion zone 126 via the tertiary fuel and air discharge ducts 134 (arrow FA3).
  • the combustion chamber walls 121, 123, 125, and 127 are integrally formed as part of the inner circumferential surface 154 of the premixer 150.
  • the combustion chamber walls are formed in a separate sleeve or interlocking sleeves, which are subsequently circumscribed by the premixer inner circumferential surface 154.
  • Compressed air flow CP and combustion backpressure BP do fluctuate temporally denoted as ACP and ⁇ in FIG. 5, leading to temporal fluctuations in the fuel-air ratio.
  • the temporal fluctuations ACP and ⁇ are also normalized by selectively varying at locations within the volume of the three- dimensional lattice web structure 160 of the premixer 150, altering the size, shape and density of the apertures or passages 162, and or the wall surfaces that form the FAMDs 108, 110, 112 and/or the fuel and air discharge ducts 130, 132, 134.
  • ACP and ⁇ are also normalized by selectively varying at locations within the volume of the three- dimensional lattice web structure 160 of the premixer 150, altering the size, shape and density of the apertures or passages 162, and or the wall surfaces that form the FAMDs 108, 110, 112 and/or the fuel and air discharge ducts 130, 132, 134.
  • premixer 170 shows a lattice-like structure of generally vertically oriented webs 172, 174, 176, and generally horizontally oriented webs 178, 180, 182, 184, 186.
  • the lattice structure of the premixer 200 comprises vertically aligned webs 202, oriented along axis Y, axially aligned webs
  • the webs 202 and 204 extend vertically along axis Y to a length L.
  • the three dimensional, hour glass-like, lattice structure of the annular premixer 210 comprises nested, generally circular webs 212, 214, 216, 218, 222, having respective radii Ri, R 2 , R 3 , R4, and vertically aligned webs 220, which collectively define apertures or passages 224.
  • Web 226 defines a generally circular passage 228.
  • the premixer 210 is formed from a stack of separate, three-dimensional, monolithic lattice structures, labeled I, II, III, IV and V. Those monolithic structures are coupled to form the completed premixer 210.
  • a premixer structure similar to premixer 210 is formed by coupling nested, concentric annular hoops (e.g., the hoop bounded by R 1 -R 2 , or R 2 -R 3 , or R 3 -R4).
  • sector-shaped wedges of three-dimensional, monolithic lattice structures are coupled to form a completed premixer.
  • separate, discrete, three-dimensional, monolithic lattice structures are coupled by welding, brazing, fasteners, and mating or interlocking web portions.
  • FIG. 10 shows exemplary localized variations in the web portions of another embodiment of a three-dimensional, monolithic lattice structure of a premixer 230.
  • Cavities of an asymmetrical, serpentine-like fuel and air mixing duct (“FAMD") 231, fuel delivery system 232, and fuel and air discharge duct 233 are formed by three- dimensional walls 236, 238 and 240. Walls 242, 244, 246, 248, 250, 252, 254, and 256 form air ducts to direct air (AIR or A) into the FAMD 231, via apertures 258, 260, 262, 264, 268, 270, 272, 274, and 276.
  • the fuel delivery system 232 introduces
  • the FAMD 231 and fuel and air discharge duct 233 collectively orient flow and cross section of the fuel and air mixture FA4, for normalizing backpressure fluctuations ⁇ .
  • FIG. 1 1 is a two-stage annular combustor of the general type shown in U. S. Patent No. 7,841, 181.
  • the combustor 300 incorporates a premixer having a monolithic, three-dimensional lattice structure in accordance with another embodiment of the invention.
  • the combustor 300 has a combustion chamber 302.
  • An upstream axial, combustion chamber wall 304 has an annular-shape, with an outer peripheral edge conjoined with a cylindrical outer wall 306, and an inner peripheral edge with an inner wall 312.
  • the inner 312 and outer 306 cylindrical walls of the combustion chamber 302 are concentrically aligned with the combustion chamber axial centerline.
  • the axial centerline of the combustion chamber 302 is coextensive with the combustor 300 axial centerline.
  • the combustion chamber 302 defines, sequentially from the axial, upstream, combustion chamber wall 304, a primary combustion zone 310 (sometimes also referred to as a main combustion zone or a main 1 combustion zone), between the inner wall 312 and the outer cylindrical wall 306 of the combustion chamber, and a secondary combustion zone 308 (sometimes also referred to as a pilot combustion zone or a main 2 combustion zone), downstream of the lower axial end wall 348 of the inner wall 312 of the combustion chamber.
  • An air intake plenum 314 provides compressed air CP to the combustion chamber 302, through the annular-shaped premixer 320.
  • the premixer 320 has a centerline that is coextensive with centerlines of the combustor 300 and the combustion chamber 302.
  • the premixer 320 has an upper axial end; a lower axial end proximate the upstream axial wall 304 of the combustion chamber 302; an inner annular wall 340 in fluid communication with the upstream axial wall of the combustion chamber; and an outer annular wall 322 in fluid communication with the air intake plenum 314.
  • the premixer 320 has a monolithic, three-dimensional lattice structure of selectively oriented, asymmetrical- and serpentine- shaped metallic webs and premixer passages formed therein.
  • the premixer passages form a first plurality of air ducts 324, oriented asymmetrically about the outer annular wall 322 of the premixer, in fluid communication with the air intake plenum 314, for selectively directing compressed air radially inwardly with respect to the premixer axial centerline and axially toward the lower axial end thereof, at selectively varying flow rates and pressures at different locations about the outer annular wall of the fuel-air premixer, for equalizing and stabilizing over time air fuel mixture within the fuel-air premixer.
  • Primary 332 and secondary 346 fuel delivery passages are respectively in fluid communication with a primary fuel delivery system 330 and a secondary fuel delivery system 344.
  • a primary fuel and air mixing duct 326 is, in fluid communication with the first plurality of air ducts 324 and the primary fuel delivery passage 332, oriented intermediate the inner 340 and outer 322 annular walls of the annular-shaped fuel-air premixer 320.
  • a primary fuel and air discharge duct 328 is in fluid communication with the primary fuel and air mixing duct 326 and is in fluid communication with the primary combustion zone 310 of the combustion chamber 302, where its fuel and air mixture FA5 is discharged through the lower axial end of the premixer 320.
  • a secondary fuel and air mixing duct 345 is in fluid communication with a secondary air mixing duct 342, the secondary fuel delivery passage 346 and a secondary fuel and air discharge duct 350.
  • the secondary fuel and air discharge duct 350 is coupled to lower axial end wall 348 of the inner wall 312 of the combustion chamber 302.
  • the secondary fuel and air discharge duct 350 is in fluid communication with the secondary combustion zone 308, where its fuel and air mixture FA6 is discharged.
  • the three-dimensional lattice structure of the premixer 320 forms the webs and passages therein to equalize and normalize fuel-air ratio in the premixer, and optionally within the combustion chamber 302, as is done in the combustors and premixers of FIGs. 5-10. While the combustor 300 is a two-stage annular combustor, its features are also applicable to single-stage annular combustors, as well as annular combustors having more than two stages. [0052] FIG.
  • FIG. 12 is another embodiment of a two-stage annular combustor 400 of the general type shown in U.S. Patent No. 8,881,531, with compressed air CP from the air intake plenum 414 entering the combustor radially around the circumferential outer periphery of the premixer 420 (similarly to the premixer 320 of FIG. 11) and additionally, axially through its upper axial end.
  • the combustor 400 incorporates a premixer 420 having a monolithic, three-dimensional lattice structure in accordance with another embodiment of the invention.
  • the combustor 400 has a combustion chamber 402, similar to the combustion chamber 302 of FIG. 11. In the embodiment of FIG.
  • the upstream axial, combustion chamber wall 404 has an annular-shape, with an outer peripheral edge conjoined with a cylindrical outer wall 406, and an inner peripheral edge with an inner wall 412.
  • the inner 412 and outer 406 cylindrical walls of the combustion chamber 402 are concentrically aligned with the combustion chamber axial centerline.
  • the axial centerline of the combustion chamber 402 is coextensive with the combustor 400 axial centerline.
  • the combustion chamber 402 defines, sequentially from the axial, upstream, combustion chamber wall 404, a primary combustion zone 410 (sometimes also referred to as a main combustion zone or a main 1 combustion zone), between the inner wall 412 and the outer cylindrical wall 406 of the combustion chamber, and a secondary combustion zone 408 (sometimes also referred to as a pilot combustion zone or a main 2 combustion zone), downstream of the lower axial end wall 448 of the inner wall 412 of the combustion chamber.
  • the air intake plenum 414 provides compressed air CP to the combustion chamber 402, through the annular-shaped premixer 420.
  • the premixer 420 has a centerline that is coextensive with centerlines of the combustor 400 and the combustion chamber 402.
  • the premixer 420 has an open, upper axial end, in communication with the air intake plenum 414, through axial air duct 425 that is formed in the lattice structure, which receives compressed air CP.
  • the premixer 420 also has a lower axial end proximate the upstream axial wall 404 of the combustion chamber 402; an inner annular wall 440 in fluid communication with the upstream axial wall 404 of the combustion chamber and the air intake plenum 414; and an outer annular wall 422 in fluid communication with the air intake plenum 414.
  • the premixer 420 has a monolithic, three-dimensional lattice structure of selectively oriented, asymmetrical- and serpentine- shaped metallic webs and premixer passages formed therein.
  • the premixer passages form a first plurality of air ducts 424, oriented asymmetrically about the outer annular wall 422 of the premixer, in fluid communication with the air intake plenum 414, for selectively directing compressed air radially inwardly with respect to the premixer axial centerline and axially toward the lower axial end thereof, at selectively varying flow rates and pressures at different locations about the outer annular wall of the premixer, for equalizing and stabilizing over time air fuel mixture within the fuel-air premixer.
  • Primary 432 and secondary 446 fuel delivery passages are respectively in fluid communication with a primary fuel delivery system 430 and a secondary fuel delivery system 444.
  • a primary fuel and air mixing duct 426 is, in fluid communication with the first plurality of air ducts 424 and the primary fuel delivery passage 432, oriented intermediate the inner 440 and outer 422 annular walls of the annular-shaped fuel-air premixer 420.
  • a primary fuel and air discharge duct 428 is in fluid communication with the primary fuel and air mixing duct 426 and is in fluid communication with the primary combustion zone 410 of the combustion chamber 402, through the lower axial end of the premixer 420, where its fuel and air mixture FA7 is discharged through the lower axial end of the premixer 420.
  • a secondary fuel and air mixing duct 445 is in fluid communication with the axial air duct 425, via a secondary air duct 442, the secondary fuel delivery passage 446 and a secondary fuel and air discharge duct 450.
  • the secondary fuel and air discharge duct 450 is coupled to the lower axial end wall 448 of the inner wall 412 of the combustion chamber 402.
  • the secondary fuel and air discharge duct 450 is in fluid communication with the secondary combustion zone 408, where its fuel and air mixture FA8 is discharged.
  • the three-dimensional lattice structure of the premixer 420 forms the webs and passages therein to equalize and normalize fuel-air ratio in the premixer, and optionally within the combustion chamber 402, as is done in the combustors and premixers of FIGs. 5-11. While the combustor 400 is a two-stage annular combustor, its features are also applicable to single-stage annular combustors, as well as annular combustors having more than two stages.
  • FIG. 13 illustrates a method for fabricating a premixer, having a monolithic, three-dimensional lattice structure of selectively oriented, asymmetrical- and serpentine- shaped metallic webs and premixer passages, such as the premixer 150 in
  • FIG. 5 in order to achieve uniform fuel-air ratio within the premixed fuel and air mixture, throughout the premixer, during steady state operation in the absence of temporal fluctuations in fuel delivery or compressor airflow, or combustion backpressure.
  • the method is also useful for fabricating a premixer, such as the premixer 150 in FIG. 5, where profiles of the various ducts and/or fuel passages is selectively altered locally within the lattice-like mesh 160, in order to deliver uniform fuel and air mixture to the combustion chamber of the combustor.
  • profiles of the various ducts and/or fuel passages is selectively altered locally within the lattice-like mesh 160 of the premixer 150, in order to normalize mass flow of combustion gasses within the volume of the combustion chamber 120.
  • step 504 operation of the modeled combustor 100, including the three- dimensional, lattice-like premixer 150, are simulated in computer workstation running commercially available computational fluid dynamics ("CFD") simulation software.
  • CFD computational fluid dynamics
  • intake air CP, fuel F, fuel and air mixture FA in the premixer 150 and combustion gas flow dynamics within the combustion chamber 120, including combustion backpressure BP dynamics within the combustion chamber and upstream into the premixer are evaluated.
  • Empirical, operational knowledge about such flow dynamics based on past physical observation and simulations are utilized to evaluate the CFD simulations. Local deviations from a desired fuel-air ratio within the fuel and air mixture, throughout the premixer volume and the sources of such deviations are identified and evaluated.
  • step 506 the premixer lattice structure, as well as structure of any other components in the combustor, are revised and altered, in order to equalize the fuel and air mixture ("F/A") throughout the combustor and normalize influence of transient fluctuations in CP and/or BP on the F/A.
  • F/A fuel and air mixture
  • localized variations in steady state airflow CP, or normalization of transient pulsations ACP within the air intake plenum 106 of FIG. 5 at different circumferential angular positions ⁇ or axial position L are compensated by altering the cross sectional dimensions or shape of air ducts leading to the locally associated fuel and air mixing ducts (FAMDs) 108, 110, 112.
  • FAMDs fuel and air mixing ducts
  • FAMDs 108, 1 10, 1 12, and their associated fuel and air discharge ducts 130, 132, 134 are locally varied to resist backpressure BP and backpressure fluctuations ⁇ .
  • Dimensions and shape of fuel and air discharge ducts 130, 132, 134 are locally varied to normalize flow of the fuel and air mixture within the combustion chamber 120 volume, and/or to normalize combustion burning in various zones 122, 124, 126 of the combustion chamber.
  • the revised combustor 100 structural model is stored in step 508 of FIG. 13.
  • step 510 of FIG. 13 the stored, revised structural model of step 508 is used to construct the premixer 150 of FIG. 5, and other combustor 100 components.
  • manufacture focus is on the premixer 150, which is constructed as a monolithic, three-dimensional lattice, metallic structure.
  • Metal alloys used to form the premixer, as well as other components within the combustor, are typically nickel/cobalt/chromium-based so-called superalloys.
  • monolithic, three-dimensional lattice structure premixers of FIGs. 5-12 are fabricated, using additive manufacture methods.
  • the premixer such as the premixer 150 of FIGs. 5 and 6, is directly constructed, layer by layer, by fusing metallic powder, with a focused energy source such as a laser, into a monolithic, three-dimensional lattice structure of selectively oriented, asymmetrical- and serpentine- shaped metallic webs and premixer passages that replicate desired ultimate structure of the premixer.
  • the monolithic, three-dimensional lattice structure premixers of FIGs. 5-12 are fabricated by a sacrificial-pattern, mold-casting process.
  • a pattern mold which replicates the structure of the desired, monolithic, three- dimensional lattice structure of selectively oriented, asymmetrical- and serpentine- shaped metallic webs and premixer passages of the premixer, is formed by an additive manufacture process, by fusing powdered mold material with an energy source.
  • the pattern mold is encased in a metal casting mold.
  • the formed mold is filled with molten metal, which displaces the sacrificial mold pattern. After the molten metal hardens, the surrounding mold is removed.
  • the completed cast-metal premixer replicates the desired, monolithic, three-dimensional lattice structure of selectively oriented, asymmetrical- and serpentine-shaped metallic webs and premixer passages.
  • the constructed premixer 150 of FIGs. 5 and 6 is assembled, with other components, into combustor 100.
  • the combustor 100 or any other previously described combustor embodiment described in this portion of this document, is then installed in a combustion turbine engine, such as the engine 20 of FIG. 1, in place of the combustor 38.

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Abstract

Chambre de combustion pour un moteur à turbine à combustion comprenant un pré-mélangeur de carburant et d'air, dont les modes de réalisation font varier localement la structure d'un ou de plusieurs de conduits d'air, de passages de distribution de carburant, de conduits de mélange de carburant et d'air, et/ou de conduits d'évacuation de carburant et d'air, afin de normaliser le rapport air-air à n'importe quel emplacement autour du volume tridimensionnel du pré-mélangeur, ou dans la chambre de combustion, pendant des conditions de fonctionnement à régime permanent, et/ou afin de stabiliser les fluctuations de l'alimentation en air comprimé vers le pré-mélangeur, et/ou afin de stabiliser les fluctuations de la contre-pression de gaz de combustion en amont dans le pré-mélangeur, ou dans la chambre de combustion. Le pré-mélangeur est une structure en treillis tridimensionnel monolithique de bandes métalliques orientées de manière sélective, asymétriques et en forme de serpentin. La structure de bande délimite des passages localement variables, qui forment : les passages et conduits d'air précités. Selon certains modes de réalisation, le pré-mélangeur, ou un moule de coulée pour le pré-mélangeur, est formé par fabrication additive.
PCT/US2017/016420 2017-02-03 2017-02-03 Chambre de combustion avec pré-mélangeur en treillis tridimensionnel WO2018144008A1 (fr)

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Application Number Priority Date Filing Date Title
PCT/US2017/016420 WO2018144008A1 (fr) 2017-02-03 2017-02-03 Chambre de combustion avec pré-mélangeur en treillis tridimensionnel
PCT/US2017/044827 WO2018144065A1 (fr) 2017-02-03 2017-08-01 Composant refroidi par air pour moteur à turbine, à réseau tridimensionnel monolithique à densité variable
PCT/US2017/044792 WO2018144064A1 (fr) 2017-02-03 2017-08-01 Panneau refroidi par air pour turbine, à treillis tridimensionnel monolithique, et son procédé de fabrication
PCT/US2018/021102 WO2019027508A1 (fr) 2017-02-03 2018-03-06 Doublure de chambre de combustion à atténuation de bruit pour moteur à turbine à combustion

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Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2020245537A1 (fr) * 2019-06-07 2020-12-10 Safran Helicopter Engines Procédé de fabrication d'un tube à flamme pour une turbomachine
FR3097029A1 (fr) * 2019-06-07 2020-12-11 Safran Helicopter Engines Procédé de fabrication d’un tube à flamme pour une turbomachine
EP4411236A1 (fr) * 2023-02-02 2024-08-07 Pratt & Whitney Canada Corp. Système de carburant avec injecteurs disposés radialement pour moteur à turbine à gaz à hydrogène
EP4411235A1 (fr) * 2023-02-02 2024-08-07 Pratt & Whitney Canada Corp. Moteur à turbine à gaz à hydrogène avec anneau d'injecteur et alimentation étagée de carburant
EP4411234A1 (fr) * 2023-02-02 2024-08-07 Pratt & Whitney Canada Corp. Moteur à turbine à gaz à hydrogène avec anneau d'injecteur

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6698206B2 (en) 1999-12-16 2004-03-02 Rolls-Royce Plc Combustion chamber
US6732527B2 (en) 2001-05-15 2004-05-11 Rolls-Royce Plc Combustion chamber
US20050076644A1 (en) * 2003-10-08 2005-04-14 Hardwicke Canan Uslu Quiet combustor for a gas turbine engine
US20080006033A1 (en) * 2005-09-13 2008-01-10 Thomas Scarinci Gas turbine engine combustion systems
WO2014105108A1 (fr) * 2012-12-28 2014-07-03 United Technologies Corporation Composant de moteur à turbine à gaz à structure maillée vasculaire artificielle
US8881531B2 (en) 2005-12-14 2014-11-11 Rolls-Royce Power Engineering Plc Gas turbine engine premix injectors
EP2930430A1 (fr) * 2014-04-07 2015-10-14 Siemens Aktiengesellschaft Bec de brûleur et brûleur d'une turbine à gaz

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6698206B2 (en) 1999-12-16 2004-03-02 Rolls-Royce Plc Combustion chamber
US6732527B2 (en) 2001-05-15 2004-05-11 Rolls-Royce Plc Combustion chamber
US20050076644A1 (en) * 2003-10-08 2005-04-14 Hardwicke Canan Uslu Quiet combustor for a gas turbine engine
US20080006033A1 (en) * 2005-09-13 2008-01-10 Thomas Scarinci Gas turbine engine combustion systems
US7841181B2 (en) 2005-09-13 2010-11-30 Rolls-Royce Power Engineering Plc Gas turbine engine combustion systems
US8881531B2 (en) 2005-12-14 2014-11-11 Rolls-Royce Power Engineering Plc Gas turbine engine premix injectors
WO2014105108A1 (fr) * 2012-12-28 2014-07-03 United Technologies Corporation Composant de moteur à turbine à gaz à structure maillée vasculaire artificielle
EP2930430A1 (fr) * 2014-04-07 2015-10-14 Siemens Aktiengesellschaft Bec de brûleur et brûleur d'une turbine à gaz

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2020245537A1 (fr) * 2019-06-07 2020-12-10 Safran Helicopter Engines Procédé de fabrication d'un tube à flamme pour une turbomachine
FR3097029A1 (fr) * 2019-06-07 2020-12-11 Safran Helicopter Engines Procédé de fabrication d’un tube à flamme pour une turbomachine
CN113924444A (zh) * 2019-06-07 2022-01-11 赛峰直升机引擎公司 制造用于涡轮机的火焰管的方法
US20220252268A1 (en) * 2019-06-07 2022-08-11 Safran Helicopter Engines Method for manufacturing a flame tube for a turbomachine
US12345418B2 (en) * 2019-06-07 2025-07-01 Safran Helicopter Engines Method for manufacturing a flame tube for a turbomachine
EP4411236A1 (fr) * 2023-02-02 2024-08-07 Pratt & Whitney Canada Corp. Système de carburant avec injecteurs disposés radialement pour moteur à turbine à gaz à hydrogène
EP4411235A1 (fr) * 2023-02-02 2024-08-07 Pratt & Whitney Canada Corp. Moteur à turbine à gaz à hydrogène avec anneau d'injecteur et alimentation étagée de carburant
EP4411234A1 (fr) * 2023-02-02 2024-08-07 Pratt & Whitney Canada Corp. Moteur à turbine à gaz à hydrogène avec anneau d'injecteur
US12298008B2 (en) 2023-02-02 2025-05-13 Pratt & Whitney Canada Corp. Fuel system with radially arranged injectors for hydrogen-driven gas turbine engine

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