WO2015134010A1 - Combustor inlet flow static mixing system for conditioning air being fed to the combustor in a gas turbine engine - Google Patents

Combustor inlet flow static mixing system for conditioning air being fed to the combustor in a gas turbine engine Download PDF

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Publication number
WO2015134010A1
WO2015134010A1 PCT/US2014/020692 US2014020692W WO2015134010A1 WO 2015134010 A1 WO2015134010 A1 WO 2015134010A1 US 2014020692 W US2014020692 W US 2014020692W WO 2015134010 A1 WO2015134010 A1 WO 2015134010A1
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WO
WIPO (PCT)
Prior art keywords
static mixing
extending
radially
arm
arms
Prior art date
Application number
PCT/US2014/020692
Other languages
French (fr)
Inventor
Richard L. THACKWAY
William R. Ryan
Original Assignee
Siemens Aktiengesellschaft
Siemens Energy, Inc.
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, Siemens Energy, Inc. filed Critical Siemens Aktiengesellschaft
Priority to PCT/US2014/020692 priority Critical patent/WO2015134010A1/en
Publication of WO2015134010A1 publication Critical patent/WO2015134010A1/en

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
    • B01F—MIXING, e.g. DISSOLVING, EMULSIFYING OR DISPERSING
    • B01F25/00—Flow mixers; Mixers for falling materials, e.g. solid particles
    • B01F25/40—Static mixers
    • B01F25/42—Static mixers in which the mixing is affected by moving the components jointly in changing directions, e.g. in tubes provided with baffles or obstructions
    • B01F25/43—Mixing tubes, e.g. wherein the material is moved in a radial or partly reversed direction
    • B01F25/431—Straight mixing tubes with baffles or obstructions that do not cause substantial pressure drop; Baffles therefor
    • B01F25/4315—Straight mixing tubes with baffles or obstructions that do not cause substantial pressure drop; Baffles therefor the baffles being deformed flat pieces of material
    • B01F25/43151—Straight mixing tubes with baffles or obstructions that do not cause substantial pressure drop; Baffles therefor the baffles being deformed flat pieces of material composed of consecutive sections of deformed flat pieces of material
    • 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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
    • B01F—MIXING, e.g. DISSOLVING, EMULSIFYING OR DISPERSING
    • B01F25/00—Flow mixers; Mixers for falling materials, e.g. solid particles
    • B01F25/40—Static mixers
    • B01F25/42—Static mixers in which the mixing is affected by moving the components jointly in changing directions, e.g. in tubes provided with baffles or obstructions
    • B01F25/43—Mixing tubes, e.g. wherein the material is moved in a radial or partly reversed direction
    • B01F25/431—Straight mixing tubes with baffles or obstructions that do not cause substantial pressure drop; Baffles therefor
    • B01F25/4315—Straight mixing tubes with baffles or obstructions that do not cause substantial pressure drop; Baffles therefor the baffles being deformed flat pieces of material
    • 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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • 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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • 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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • 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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing

Definitions

  • This invention is directed generaliy to turbine engines, and more particularly to combustor air feed systems for turbine engines.
  • gas turbine engines typically include a compressor for compressing air, a combustor for mixing the compressed air with fuel and igniting the mixture, and a turbine blade assembly for producing power.
  • Compressed air is feed to a plurality of combustors via plenums.
  • Combustors often operate at high temperatures that may exceed 2,500 degrees Fahrenheit. Combustion produces NOx as a byproduct.
  • This invention relates to a compressor exhaust flow static mixing system formed from one or more radially inward extending static mixing arms and one or more radially outward extending static mixing arms that change the flow pattern of compressor exhaust flowing to the combustor is disclosed.
  • the compressor exhaust flow static mixing system creates a uniform flow distribution into the burner with a low pressure.
  • the radially inward extending static mixing arms and radially outward extending static mixing arms may be configured such that various portions of the static mixing arms are aligned with each other to create a consistent flow path within a compressor exhaust plenum.
  • a combustor inlet static mixing system formed from first and second radially extending support arms having circumferentially extending static mixing arms extending therefrom is disclosed.
  • the combustor inlet static mixing system creates a high degree of turbulence within the compressed air flow, which enhances the mixing of air and fuel, making the mixture more uniform, thereby eliminating high NOx production zones.
  • the combustor inlet static mixing system may include a plurality of first and second radially extending support arms extending radially about an annular combustor inlet.
  • the circumferentially extending static mixing arms may increase in size moving radially outward within the combustor inlet while keeping the aspect ratio of the static mixing arms constant.
  • a turbine engine may include at least one combustor positioned upstream from a rotor assembly.
  • the rotor assembly may include at least one row of turbine blades extending radially outward from a rotor.
  • a compressor may be positioned upstream from the combustor.
  • One or more compressor exhaust plenums may extend between the compressor and the combustor.
  • the turbine engine may include one or more compressor exhaust flow static mixing systems formed from at least one radially inward extending static mixing arm extending from an outer wall toward an opposing inner wall forming the compressor exhaust plenum and at least one radially outward extending static mixing arm extending from the inner wall toward the outer wall.
  • a first side of the radially inward extending static mixing arm may be nonparallel and nonorthogonal relative to a second side on an opposite side of the radially inward extending static mixing arm.
  • the first and second sides may extend from a base to a tip, and the first and second sides may be positioned such that the tip of radially inward extending static mixing arm has a width that is narrower than a width of the base of the radially inward extending static mixing arm.
  • a first side of the radially outward extending static mixing arm may be nonparallel and nonorthogonal relative to a second side on an opposite side of the radially outward extending static mixing arm.
  • the first and second sides may extend from a base to a tip, and the first and second sides may be positioned such that the tip of the radially outward extending static mixing arm has a width that is narrower than a width of the base of the radially outward extending static mixing arm.
  • a tip of the radially inward extending static mixing arm may be positioned closer to the inner wall from which the radially outward extending static mixing arm extends than a tip of the radially outward extending static mixing arm.
  • the radially inward extending static mixing arm may be offset laterally relative to a longitudinal axis of the compressor exhaust plenum from the radially outward extending static mixing arm,
  • a first side of the radially inward extending static mixing arm may be aligned with a second side of the at least one radially outward extending static mixing arm.
  • a cross-section of the flow path established by the at least one compressor exhaust flow static mixing system has a consistent width when measured orthogonally from a surface forming one of the at least one radially inward extending static mixing arm, the at least one radially outward extending static mixing arm, the inner wall and the outer wall.
  • the radially inward extending static mixing arm may have a linear tip, and the radially outward extending static mixing arm may have a linear tip.
  • the radially inward extending static mixing arm may be positioned in a portion of the compressor exhaust plenum that is formed at the inner wall from a diffuser lip and at the outer wall from a combustor liner.
  • the compressor exhaust plenum formed between the inner wall formed from the diffuser lip and the outer wall formed from the combustor liner may be in the shape of an annulus.
  • the turbine engine may include one or more combustors positioned upstream from a rotor assembly, wherein the rotor assembly may include at least one row of turbine blades extending radially outward from a rotor.
  • the turbine engine may also include a compressor positioned upstream from the at least one combustor and one or more compressor exhaust plenums extending between the compressor and the combustor.
  • One or more combustor inlet static mixing systems may be formed from a first radially extending support arm
  • first circumferentially extending static mixing arms may extend from the first radially extending support arm toward the second radially extending support arm and one or more second circumferentially extending static mixing arms may extend from the second radially extending support arm toward the first radially extending support arm.
  • the second circumferentially extending static mixing arm may be positioned further radially outward than the first circumferentially extending static mixing arm and the second circumferentially extending static mixing arm may be larger than the at least one first circumferentially extending static mixing arm.
  • the combustor inlet static mixing system may include a plurality of first radially extending support arms and a plurality of second radially extending support arms extending radially around an annular combustor inlet.
  • the first radially extending support arm may include a plurality of first circumferentially extending static mixing arms extending toward the second radially extending support arm
  • the second radially extending support arm may include a plurality of second circumferentially extending static mixing arms extending toward the first radially extending support arm.
  • the first and second circumferentially extending static mixing arms may be offset from each other radially, and the first and second circumferentially extending static mixing arms may increase in size moving radially outward.
  • the combustor inlet static mixing system may include plurality of first radially extending support arms and a plurality of second radially extending support arms extending radially around an annular combustor inlet.
  • Each of the plurality of first radially extending support arms may include a plurality of first circumferentially extending static mixing arms and each of the plurality of second radially extending support arms may include a plurality of second circumferentially extending static mixing arms.
  • the first and second circumferentially extending static mixing arms on each first and second radially extending support arms may be offset from each other radially, and the first and second
  • circumferentially extending static mixing arms may increase in size moving radially outward.
  • An advantage of the compressor exhaust flow static mixing system is that the system conditions the compressed air flow to produce uniform flow with a lower pressure loss relative to a conventional high pressure loss flow conditioner.
  • compressor exhaust flow static mixing system Another advantage of the compressor exhaust flow static mixing system is that the system static mixing arms are angled with a narrower tip at the tip than the base of the static mixing arms which creates a high level of turbulence that redistributes the flow.
  • An advantage of the combustor inlet static mixing system is that the system creates a high degree of turbulence within the compressed air flow, which enhances the mixing of air and fuel, making the mixture more uniform, thereby eliminating high NOx production zones.
  • combustor inlet static mixing system Another advantage of the combustor inlet static mixing system is that the system can produce a constant blockage factor from tip to hub by holding the aspect ratio of each static mixing arm constant and by positioning each static mixing arm at the same angle relative to the flow of compressed air.
  • Figure 1 is a cross-sectional side view of a portion of a turbine engine including a compressor, a combustor, a rotor assembly and a compressor exhaust flow static mixing system.
  • Figure 2 is a cross-sectional side view of a combustor plenum with the compressor exhaust flow static mixing system shown in Figure 1 .
  • Figure 3 is a downstream view of static mixing arms of the compressor exhaust flow static mixing system shown in Figure 1 .
  • Figure 4 is a cross-sectional side view of a portion of a turbine engine including a compressor, a combustor, a rotor assembly and a combustor inlet static mixing system.
  • Figure 5 is a cross-sectional side view of a combustor inlet of an annular combustor with the combustor inlet static mixing system.
  • Figure 6 is a partial detailed end view of the combustor inlet static mixing system of Figure 4.
  • Figure 7 is a partial cross-sectional side view of the combustor inlet static mixing system of Figure 4.
  • a compressor exhaust flow static mixing system 10 formed from one or more radially inward extending static mixing arms 12 and one or more radially outward extending static mixing arms 14 that change the flow pattern of compressor exhaust flowing to the combustor 16 is disclosed.
  • the compressor exhaust flow static mixing system 10 creates a uniform flow distribution into the burner with a low pressure.
  • the radially inward extending static mixing arms 12 and radially outward extending static mixing arms 14 may be configured such that various portions of the static mixing arms 12, 14 are aligned with each other to create a consistent flow path within a compressor exhaust plenum 18.
  • a combustor inlet static mixing system 100 formed from first and second radially extending support arms 102, 104 having circumferentiaily extending static mixing arms 106 extending therefrom is disclosed.
  • the combustor inlet static mixing system 100 creates a high degree of turbulence within the compressed air flow, which enhances the mixing of air and fuel, making the mixture more uniform, thereby eliminating high NOx production zones.
  • the combustor inlet static mixing system 100 may include a plurality of first and second radially extending support arms 102, 104 extending radially about an annular combustor inlet 108.
  • the circumferentiaily extending static mixing arms 106 may increase in size moving radially outward within the combustor inlet 108 while keeping the aspect ratio of the static mixing arms constant.
  • a turbine engine 20 including the system 10 may include one or more combustors 16 positioned upstream from a rotor assembly 24.
  • the rotor assembly 24 may include one or more rows of turbine blades 26 extending radially outward from a rotor 28.
  • the turbine engine 20 may include a compressor 30 positioned upstream from the combustor 16.
  • One or more compressor exhaust plenums 18 may extend between the compressor 30 and the combustor 16.
  • the turbine engine 20 may also include the compressor exhaust flow static mixing system 10 formed from one or more radially inward extending static mixing arms 12 extending from an outer wall 32 toward an opposing inner wall 34 forming the compressor exhaust plenum 18 and at least one radially outward extending static mixing arm 14 extending from the inner wall 34 toward the outer wall 32.
  • first side 36 of the radially inward extending static mixing arm 12 may be nonparallel and nonorthogonal relative to a second side 38 on an opposite side of the radially inward extending static mixing arm 12.
  • the first and second sides 36, 38 may extend from a base 40 to a tip 42 and where the first and second sides 36, 38 may be positioned such that the tip 42 of the radially inward extending static mixing arm 12 has a width 44 that is narrower than a width 46 of the base 40 of the radially inward extending static mixing arm 12.
  • the first and second sides 36, 38 may be linear, curved, a combination of linear and curved sections or any other appropriate configuration.
  • a first side 48 of the radially outward extending static mixing arm 14 may be nonpara!lel and nonorthogonal relative to a second side 50 on an opposite side of the radially outward extending static mixing arm 14.
  • the first and second sides 48, 50 may extend from a base 56 to a tip 58.
  • the first and second sides 48, 50 may be positioned such that the tip 58 of the radially outward extending static mixing arm 14 may have a width 52 that is narrower than a width 54 of the base 56 of the radially outward extending static mixing arm 14.
  • the first and second sides 48, 50 may be linear, curved, a combination of linear and curved sections or any other appropriate configuration.
  • a tip 42 of the radially inward extending static mixing arm 12 may be positioned closer to the inner wall 34 from which the radially outward extending static mixing arm 14 extends than a tip 58 of the radially outward extending static mixing arm 14.
  • a tip 58 of the radially outward extending static mixing arm 14 may be positioned closer to the outer wall 32 from which the radially outward extending static mixing arm 14 extends than a tip 42 of the radially inward extending static mixing arm 12.
  • the radially inward extending static mixing arm 12 may be offset laterally relative to a longitudinal axis 60 of the compressor exhaust plenum 18 from the radially outward extending static mixing arm 14.
  • first side 36 of the radially inward extending static mixing arm 12 may be aligned with the second side 38 of an adjacent radially outward extending static mixing arm 14, as shown in Figure 3.
  • a cross-section of a flow path 62 established by the compressor exhaust flow static mixing system 10 may have a consistent width 64 when measured orthogonally from a surface 66 forming one of the radially inward extending static mixing arm 12, the at least one radially outward extending static mixing arm 14, the inner wall 34 and the outer wall 32.
  • the radially inward extending static mixing arm 12 may have a linear tip 42.
  • the radially outward extending static mixing arm 14 may have a linear tip 58.
  • the radially inward extending static mixing arm 12 may have tip 42 with an alternative configuration.
  • the radially outward extending static mixing arm 14 may have tip 58 with an alternative configuration.
  • the radially inward extending static mixing arm 12 may be positioned in a portion 67 of the compressor exhaust plenum 18 that is formed at the inner wall 34 from a diffuser lip 68 and at the outer wall 32 from a combustor liner 70.
  • the compressor exhaust plenum 18 may be formed between the inner wall 34 formed from the diffuser lip 68 and the outer wall 32 formed from the combustor liner 70 is in the shape of an annulus.
  • the compressor exhaust plenum 18 may have an annular shape.
  • compressed air flows through the compressor exhaust flow static mixing system 10 formed from one or more radially inward extending static mixing arms 12 and one or more radially outward extending static mixing arms 14 that change the flow pattern of compressor exhaust flowing to the combustor 16.
  • the compressor exhaust flow static mixing system 10 creates a uniform flow distribution into the burner with a low pressure.
  • the turbine engine 20 may include one combustor 16 positioned upstream from the rotor assembly 24.
  • the rotor assembly 24 may include one or more rows of turbine blades 26 extending radially outward from the rotor 28.
  • the compressor 30 may be positioned upstream from the combustor 16.
  • One or more compressor exhaust plenums 18 may extend between the compressor 30 and the combustor 16.
  • a combustor inlet static mixing system 100 may be formed from a first radially extending support arm 102
  • a first circumferentialiy extending static mixing arm 1 10 may extend from the first radially extending support arm 102 toward the second radially extending support arm 104.
  • a second circumferentially extending static mixing arm 1 12 may extend from the second radially extending support arm 104 toward the first radially extending support arm 102.
  • the second circumferentially extending static mixing arm 112 may be positioned further radially outward than the first circumferentially extending static mixing arm 1 10.
  • the second circumferentially extending static mixing arm 112 may be larger than the first circumferentially extending static mixing arm 1 10.
  • the combustor inlet static mixing system 100 may include a plurality of first radially extending support arms 102 and a plurality of second radially extending support arms 104 extending radially around an annular combustor inlet 108.
  • the first radially extending support arm 102 may include a plurality of first circumferential!y extending static mixing arms 1 10 extending toward the second radially extending support arm 104, and a plurality of second circumferentially extending static mixing arms 1 12 extending toward the first radially extending support arm 102.
  • the first and second circumferentially extending static mixing arms 110, 1 12 may be offset from each other radially.
  • the first and second circumferentially extending static mixing arms 1 10, 1 12 may increase in size moving radially outward. By increasing in size moving radially outward, the size of the flow path 1 14 may be kept constant, thereby keeping the flow through the flow path 1 14 consistent.
  • the combustor inlet static mixing system 100 may include a plurality of first radially extending support arms 102 and a plurality of second radially extending support arms 104 extending radially around an annular combustor inlet 108.
  • Each of the plurality of first radially extending support arms 102 may include a plurality of first circumferentially extending static mixing arms 110 and each of the plurality of second radially extending support arms 104 may include a plurality of second circumferentially extending static mixing arms 1 12.
  • the first and second circumferentially extending static mixing arms 1 10, 1 12 on each first and second radially extending support arms 102, 104 may be offset from each other radially.
  • the first and second circumferentially extending static mixing arms 1 10, 1 12 may increase in size moving radially outward.
  • the first and second circumferentially extending static mixing arms 1 10, 1 12 may be nonorthogonal and nonparallel to a direction of flow 120.
  • the first and second circumferentially extending static mixing arms 1 10, 1 12 may be angled in a downstream direction such that bases 124, 128 of the first and second circumferentially extending static mixing arms 1 10, 1 12 may be positioned further upstream than tips 128, 130 of the first and second circumferentially extending static mixing arms 110, 1 12.
  • the first and second circumferentially extending static mixing arms 1 10, 112 may be positioned at an angle 122 of more than zero degrees and less than 90 degrees.
  • the first and second circumferentially extending static mixing arms 1 10, 112 may be positioned at an angle 122 relative to the direction of flow 120 of between about 15 degrees and about 45 degrees.
  • compressed air flows into the combustor inlet static mixing system 100 formed from first and second radially extending support arms 102, 104 having circumferentially extending static mixing arms 106 extending therefrom.
  • the combustor inlet static mixing system 100 creates a high degree of turbulence within the compressed air flow, which enhances the mixing of air and fuel, making the mixture more uniform, thereby eliminating high NOx production zones.
  • the combustor inlet static mixing system 100 may include a plurality of first and second radially extending support arms 102, 104 extending radially about an annular combustor inlet 108.
  • the circumferentially extending static mixing arms 106 may increase in size moving radially outward within the combustor inlet 108 while keeping the aspect ratio of the static mixing arms constant.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Dispersion Chemistry (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

A gas turbine engine comprising a compressor exhaust flow static mixing system (10) formed from one or more radially inward extending static mixing arms (12) and one or more radially outward extending static mixing arms (14) that change the flow pattern of compressor exhaust flowing to the combustor (16). The radially inward extending static mixing arms (12) and radially outward extending static mixing arms (14) may be configured such that various portions of the static mixing arms (12, 14) are aligned with each other to create a consistent flow path. The gas turbine engine further comprising a combustor inlet static mixing system formed from first and second radially extending support arms having circumferentially extending static mixing arms extending therefrom. The combustor inlet static mixing system includes a plurality of first and second radially extending support arms extending radially about an annular combustor inlet. The circumferentially extending static mixing arms may increase in size moving radially outward within the combustor inlet.

Description

COMBUSTOR UNLET FLOW STATIC MIXING SYSTEM FOR CONDITIONING AIR BEING FED TO THE COMBUSTOR IN A GAS TURBINE ENGINE
FIELD OF THE INVENTION
This invention is directed generaliy to turbine engines, and more particularly to combustor air feed systems for turbine engines.
BACKGROUND
Typically, gas turbine engines include a compressor for compressing air, a combustor for mixing the compressed air with fuel and igniting the mixture, and a turbine blade assembly for producing power. Compressed air is feed to a plurality of combustors via plenums. Combustors often operate at high temperatures that may exceed 2,500 degrees Fahrenheit. Combustion produces NOx as a byproduct.
Efforts have been made to reduce the amount of NOx produced by gas turbine engines by relying on learvpremixed combustor designs to reduce flame
temperatures.
SUMMARY OF THE INVENTION
This invention relates to a compressor exhaust flow static mixing system formed from one or more radially inward extending static mixing arms and one or more radially outward extending static mixing arms that change the flow pattern of compressor exhaust flowing to the combustor is disclosed. The compressor exhaust flow static mixing system creates a uniform flow distribution into the burner with a low pressure. The radially inward extending static mixing arms and radially outward extending static mixing arms may be configured such that various portions of the static mixing arms are aligned with each other to create a consistent flow path within a compressor exhaust plenum. A combustor inlet static mixing system formed from first and second radially extending support arms having circumferentially extending static mixing arms extending therefrom is disclosed. The combustor inlet static mixing system creates a high degree of turbulence within the compressed air flow, which enhances the mixing of air and fuel, making the mixture more uniform, thereby eliminating high NOx production zones. The combustor inlet static mixing system may include a plurality of first and second radially extending support arms extending radially about an annular combustor inlet. The circumferentially extending static mixing arms may increase in size moving radially outward within the combustor inlet while keeping the aspect ratio of the static mixing arms constant.
A turbine engine may include at least one combustor positioned upstream from a rotor assembly. The rotor assembly may include at least one row of turbine blades extending radially outward from a rotor. A compressor may be positioned upstream from the combustor. One or more compressor exhaust plenums may extend between the compressor and the combustor. The turbine engine may include one or more compressor exhaust flow static mixing systems formed from at least one radially inward extending static mixing arm extending from an outer wall toward an opposing inner wall forming the compressor exhaust plenum and at least one radially outward extending static mixing arm extending from the inner wall toward the outer wall.
A first side of the radially inward extending static mixing arm may be nonparallel and nonorthogonal relative to a second side on an opposite side of the radially inward extending static mixing arm. The first and second sides may extend from a base to a tip, and the first and second sides may be positioned such that the tip of radially inward extending static mixing arm has a width that is narrower than a width of the base of the radially inward extending static mixing arm. Similarly, a first side of the radially outward extending static mixing arm may be nonparallel and nonorthogonal relative to a second side on an opposite side of the radially outward extending static mixing arm. The first and second sides may extend from a base to a tip, and the first and second sides may be positioned such that the tip of the radially outward extending static mixing arm has a width that is narrower than a width of the base of the radially outward extending static mixing arm.
A tip of the radially inward extending static mixing arm may be positioned closer to the inner wall from which the radially outward extending static mixing arm extends than a tip of the radially outward extending static mixing arm. The radially inward extending static mixing arm may be offset laterally relative to a longitudinal axis of the compressor exhaust plenum from the radially outward extending static mixing arm, A first side of the radially inward extending static mixing arm may be aligned with a second side of the at least one radially outward extending static mixing arm. A cross-section of the flow path established by the at least one compressor exhaust flow static mixing system has a consistent width when measured orthogonally from a surface forming one of the at least one radially inward extending static mixing arm, the at least one radially outward extending static mixing arm, the inner wall and the outer wall. The radially inward extending static mixing arm may have a linear tip, and the radially outward extending static mixing arm may have a linear tip. The radially inward extending static mixing arm may be positioned in a portion of the compressor exhaust plenum that is formed at the inner wall from a diffuser lip and at the outer wall from a combustor liner. The compressor exhaust plenum formed between the inner wall formed from the diffuser lip and the outer wall formed from the combustor liner may be in the shape of an annulus.
In another embodiment, the turbine engine may include one or more combustors positioned upstream from a rotor assembly, wherein the rotor assembly may include at least one row of turbine blades extending radially outward from a rotor. The turbine engine may also include a compressor positioned upstream from the at least one combustor and one or more compressor exhaust plenums extending between the compressor and the combustor. One or more combustor inlet static mixing systems may be formed from a first radially extending support arm
circumferentially spaced from a second radially extending support arm. One or more first circumferentially extending static mixing arms may extend from the first radially extending support arm toward the second radially extending support arm and one or more second circumferentially extending static mixing arms may extend from the second radially extending support arm toward the first radially extending support arm. The second circumferentially extending static mixing arm may be positioned further radially outward than the first circumferentially extending static mixing arm and the second circumferentially extending static mixing arm may be larger than the at least one first circumferentially extending static mixing arm.
The combustor inlet static mixing system may include a plurality of first radially extending support arms and a plurality of second radially extending support arms extending radially around an annular combustor inlet. The first radially extending support arm may include a plurality of first circumferentially extending static mixing arms extending toward the second radially extending support arm, and the second radially extending support arm may include a plurality of second circumferentially extending static mixing arms extending toward the first radially extending support arm. The first and second circumferentially extending static mixing arms may be offset from each other radially, and the first and second circumferentially extending static mixing arms may increase in size moving radially outward.
In at least one embodiment, the combustor inlet static mixing system may include plurality of first radially extending support arms and a plurality of second radially extending support arms extending radially around an annular combustor inlet. Each of the plurality of first radially extending support arms may include a plurality of first circumferentially extending static mixing arms and each of the plurality of second radially extending support arms may include a plurality of second circumferentially extending static mixing arms. The first and second circumferentially extending static mixing arms on each first and second radially extending support arms may be offset from each other radially, and the first and second
circumferentially extending static mixing arms may increase in size moving radially outward.
An advantage of the compressor exhaust flow static mixing system is that the system conditions the compressed air flow to produce uniform flow with a lower pressure loss relative to a conventional high pressure loss flow conditioner.
Another advantage of the compressor exhaust flow static mixing system is that the system static mixing arms are angled with a narrower tip at the tip than the base of the static mixing arms which creates a high level of turbulence that redistributes the flow.
An advantage of the combustor inlet static mixing system is that the system creates a high degree of turbulence within the compressed air flow, which enhances the mixing of air and fuel, making the mixture more uniform, thereby eliminating high NOx production zones.
Another advantage of the combustor inlet static mixing system is that the system can produce a constant blockage factor from tip to hub by holding the aspect ratio of each static mixing arm constant and by positioning each static mixing arm at the same angle relative to the flow of compressed air.
These and other embodiments are described in more detaii beiow.
BRIEF DESCRIPTION OF THE DRAWINGS
The accompanying drawings, which are incorporated in and form a part of the specification, illustrate embodiments of the presently disclosed invention and, together with the description, disclose the principles of the invention.
Figure 1 is a cross-sectional side view of a portion of a turbine engine including a compressor, a combustor, a rotor assembly and a compressor exhaust flow static mixing system.
Figure 2 is a cross-sectional side view of a combustor plenum with the compressor exhaust flow static mixing system shown in Figure 1 .
Figure 3 is a downstream view of static mixing arms of the compressor exhaust flow static mixing system shown in Figure 1 .
Figure 4 is a cross-sectional side view of a portion of a turbine engine including a compressor, a combustor, a rotor assembly and a combustor inlet static mixing system.
Figure 5 is a cross-sectional side view of a combustor inlet of an annular combustor with the combustor inlet static mixing system.
Figure 6 is a partial detailed end view of the combustor inlet static mixing system of Figure 4.
Figure 7 is a partial cross-sectional side view of the combustor inlet static mixing system of Figure 4.
DETAILED DESCRIPTION OF THE INVENTION
As shown in Figures 1 -3, a compressor exhaust flow static mixing system 10 formed from one or more radially inward extending static mixing arms 12 and one or more radially outward extending static mixing arms 14 that change the flow pattern of compressor exhaust flowing to the combustor 16 is disclosed. The compressor exhaust flow static mixing system 10 creates a uniform flow distribution into the burner with a low pressure. The radially inward extending static mixing arms 12 and radially outward extending static mixing arms 14 may be configured such that various portions of the static mixing arms 12, 14 are aligned with each other to create a consistent flow path within a compressor exhaust plenum 18. As shown in Figures 4-7, a combustor inlet static mixing system 100 formed from first and second radially extending support arms 102, 104 having circumferentiaily extending static mixing arms 106 extending therefrom is disclosed. The combustor inlet static mixing system 100 creates a high degree of turbulence within the compressed air flow, which enhances the mixing of air and fuel, making the mixture more uniform, thereby eliminating high NOx production zones. The combustor inlet static mixing system 100 may include a plurality of first and second radially extending support arms 102, 104 extending radially about an annular combustor inlet 108. The circumferentiaily extending static mixing arms 106 may increase in size moving radially outward within the combustor inlet 108 while keeping the aspect ratio of the static mixing arms constant.
As shown in Figures 1 -3, a turbine engine 20 including the system 10 may include one or more combustors 16 positioned upstream from a rotor assembly 24. The rotor assembly 24 may include one or more rows of turbine blades 26 extending radially outward from a rotor 28. The turbine engine 20 may include a compressor 30 positioned upstream from the combustor 16. One or more compressor exhaust plenums 18 may extend between the compressor 30 and the combustor 16. The turbine engine 20 may also include the compressor exhaust flow static mixing system 10 formed from one or more radially inward extending static mixing arms 12 extending from an outer wall 32 toward an opposing inner wall 34 forming the compressor exhaust plenum 18 and at least one radially outward extending static mixing arm 14 extending from the inner wall 34 toward the outer wall 32.
As shown in Figure 3, first side 36 of the radially inward extending static mixing arm 12 may be nonparallel and nonorthogonal relative to a second side 38 on an opposite side of the radially inward extending static mixing arm 12. The first and second sides 36, 38 may extend from a base 40 to a tip 42 and where the first and second sides 36, 38 may be positioned such that the tip 42 of the radially inward extending static mixing arm 12 has a width 44 that is narrower than a width 46 of the base 40 of the radially inward extending static mixing arm 12. The first and second sides 36, 38 may be linear, curved, a combination of linear and curved sections or any other appropriate configuration.
A first side 48 of the radially outward extending static mixing arm 14 may be nonpara!lel and nonorthogonal relative to a second side 50 on an opposite side of the radially outward extending static mixing arm 14. The first and second sides 48, 50 may extend from a base 56 to a tip 58. The first and second sides 48, 50 may be positioned such that the tip 58 of the radially outward extending static mixing arm 14 may have a width 52 that is narrower than a width 54 of the base 56 of the radially outward extending static mixing arm 14. The first and second sides 48, 50 may be linear, curved, a combination of linear and curved sections or any other appropriate configuration.
In at least one embodiment, a tip 42 of the radially inward extending static mixing arm 12 may be positioned closer to the inner wall 34 from which the radially outward extending static mixing arm 14 extends than a tip 58 of the radially outward extending static mixing arm 14. Similarly, a tip 58 of the radially outward extending static mixing arm 14 may be positioned closer to the outer wall 32 from which the radially outward extending static mixing arm 14 extends than a tip 42 of the radially inward extending static mixing arm 12. The radially inward extending static mixing arm 12 may be offset laterally relative to a longitudinal axis 60 of the compressor exhaust plenum 18 from the radially outward extending static mixing arm 14. As such, the first side 36 of the radially inward extending static mixing arm 12 may be aligned with the second side 38 of an adjacent radially outward extending static mixing arm 14, as shown in Figure 3. A cross-section of a flow path 62 established by the compressor exhaust flow static mixing system 10 may have a consistent width 64 when measured orthogonally from a surface 66 forming one of the radially inward extending static mixing arm 12, the at least one radially outward extending static mixing arm 14, the inner wall 34 and the outer wall 32.
The radially inward extending static mixing arm 12 may have a linear tip 42. The radially outward extending static mixing arm 14 may have a linear tip 58. In other embodiments, the radially inward extending static mixing arm 12 may have tip 42 with an alternative configuration. Similarly, the radially outward extending static mixing arm 14 may have tip 58 with an alternative configuration. The radially inward extending static mixing arm 12 may be positioned in a portion 67 of the compressor exhaust plenum 18 that is formed at the inner wall 34 from a diffuser lip 68 and at the outer wall 32 from a combustor liner 70. The compressor exhaust plenum 18 may be formed between the inner wall 34 formed from the diffuser lip 68 and the outer wall 32 formed from the combustor liner 70 is in the shape of an annulus. Thus, the compressor exhaust plenum 18 may have an annular shape.
During use, compressed air flows through the compressor exhaust flow static mixing system 10 formed from one or more radially inward extending static mixing arms 12 and one or more radially outward extending static mixing arms 14 that change the flow pattern of compressor exhaust flowing to the combustor 16. The compressor exhaust flow static mixing system 10 creates a uniform flow distribution into the burner with a low pressure.
In another embodiment, as shown in Figures 4-7, the turbine engine 20 may include one combustor 16 positioned upstream from the rotor assembly 24. The rotor assembly 24 may include one or more rows of turbine blades 26 extending radially outward from the rotor 28. The compressor 30 may be positioned upstream from the combustor 16. One or more compressor exhaust plenums 18 may extend between the compressor 30 and the combustor 16. A combustor inlet static mixing system 100 may be formed from a first radially extending support arm 102
circumferentially spaced from a second radially extending support arm 104. A first circumferentialiy extending static mixing arm 1 10 may extend from the first radially extending support arm 102 toward the second radially extending support arm 104. A second circumferentially extending static mixing arm 1 12 may extend from the second radially extending support arm 104 toward the first radially extending support arm 102. The second circumferentially extending static mixing arm 112 may be positioned further radially outward than the first circumferentially extending static mixing arm 1 10. The second circumferentially extending static mixing arm 112 may be larger than the first circumferentially extending static mixing arm 1 10.
In one embodiment, as shown in Figure 6, the combustor inlet static mixing system 100 may include a plurality of first radially extending support arms 102 and a plurality of second radially extending support arms 104 extending radially around an annular combustor inlet 108. The first radially extending support arm 102 may include a plurality of first circumferential!y extending static mixing arms 1 10 extending toward the second radially extending support arm 104, and a plurality of second circumferentially extending static mixing arms 1 12 extending toward the first radially extending support arm 102. The first and second circumferentially extending static mixing arms 110, 1 12 may be offset from each other radially. The first and second circumferentially extending static mixing arms 1 10, 1 12 may increase in size moving radially outward. By increasing in size moving radially outward, the size of the flow path 1 14 may be kept constant, thereby keeping the flow through the flow path 1 14 consistent.
As shown in Figure 6, the combustor inlet static mixing system 100 may include a plurality of first radially extending support arms 102 and a plurality of second radially extending support arms 104 extending radially around an annular combustor inlet 108. Each of the plurality of first radially extending support arms 102 may include a plurality of first circumferentially extending static mixing arms 110 and each of the plurality of second radially extending support arms 104 may include a plurality of second circumferentially extending static mixing arms 1 12. The first and second circumferentially extending static mixing arms 1 10, 1 12 on each first and second radially extending support arms 102, 104 may be offset from each other radially. The first and second circumferentially extending static mixing arms 1 10, 1 12 may increase in size moving radially outward.
As shown in Figure 7, the first and second circumferentially extending static mixing arms 1 10, 1 12 may be nonorthogonal and nonparallel to a direction of flow 120. The first and second circumferentially extending static mixing arms 1 10, 1 12 may be angled in a downstream direction such that bases 124, 128 of the first and second circumferentially extending static mixing arms 1 10, 1 12 may be positioned further upstream than tips 128, 130 of the first and second circumferentially extending static mixing arms 110, 1 12. The first and second circumferentially extending static mixing arms 1 10, 112 may be positioned at an angle 122 of more than zero degrees and less than 90 degrees. In at least one embodiment, the first and second circumferentially extending static mixing arms 1 10, 112 may be positioned at an angle 122 relative to the direction of flow 120 of between about 15 degrees and about 45 degrees. During use, compressed air flows into the combustor inlet static mixing system 100 formed from first and second radially extending support arms 102, 104 having circumferentially extending static mixing arms 106 extending therefrom. The combustor inlet static mixing system 100 creates a high degree of turbulence within the compressed air flow, which enhances the mixing of air and fuel, making the mixture more uniform, thereby eliminating high NOx production zones. The combustor inlet static mixing system 100 may include a plurality of first and second radially extending support arms 102, 104 extending radially about an annular combustor inlet 108. The circumferentially extending static mixing arms 106 may increase in size moving radially outward within the combustor inlet 108 while keeping the aspect ratio of the static mixing arms constant.
The foregoing is provided for purposes of illustrating, explaining, and describing embodiments of this invention. Modifications and adaptations to these embodiments will be apparent to those skilled in the art and may be made without departing from the scope or spirit of this invention.

Claims

CLAIMS ! claim:
1 . A turbine engine (20), characterized in that:
at least one combustor (16) positioned upstream from a rotor assembly (24), wherein the rotor assembly (24) includes at least one row of turbine blades (26) extending radially outward from a rotor (28);
a compressor (30) positioned upstream from the at least one combustor (18); at least one compressor exhaust plenum (18) extending between the compressor (30) and the at least one combustor (16);
at least one combustor inlet static mixing system (100) formed from a first radially extending support arm (102) circurnferentially spaced from a second radially extending support arm (104), wherein at least one first circurnferentially extending static mixing arm (1 10) extends from the first radially extending support arm (102) toward the second radially extending support arm (104) and wherein at least one second circurnferentially extending static mixing arm (1 12) extends from the second radially extending support arm (104) toward the first radially extending support arm (102); and
wherein the at least one second circurnferentially extending static mixing arm (112) is positioned further radially outward than the at least one first circurnferentially extending static mixing arm (1 10) and wherein the at least one second
circurnferentially extending static mixing arm (112) is larger than the at least one first circurnferentially extending static mixing arm (1 10).
2. The turbine engine (20) of claim 1 , characterized in that the at least one combustor inlet static mixing system (100) comprises a plurality of first radially extending support arms (102) and a plurality of second radially extending support arms (104) extending radially around an annular combustor inlet (108).
3. The turbine engine (20) of claim 1 , characterized in that the at least one first radially extending support arm (102) comprises a plurality of first
circurnferentially extending static mixing arms (1 10) extending toward the at least one second radially extending support arm (104), and wherein the at least one second radially extending support arm (104) comprises a plurality of second circumferentially extending static mixing arms (1 12) extending toward the at least one first radially extending support arm (102), wherein the first and second
circumferentially extending static mixing arms (110, 1 12) are offset from each other radially and wherein the first and second circumferentially extending static mixing arms (110, 112) increase in size moving radially outward.
4. The turbine engine (20) of claim 3, characterized in that the at least one combustor inlet static mixing system (100) comprises a plurality of first radially extending support arms (102) and a plurality of second radially extending support arms (104) extending radially around an annular combustor inlet (108), and wherein each of the plurality of first radially extending support arms (102) includes a plurality of first circumferentially extending static mixing arms (1 10) and each of the plurality of second radially extending support arms (104) includes a plurality of second circumferentially extending static mixing arms (1 12).
5. The turbine engine (20) of claim 4, characterized in that the first and second circumferentially extending static mixing arms (110, 1 12) on each first and second radially extending support arms (102, 104) are offset from each other radially and wherein the first and second circumferentially extending static mixing arms (1 10, 1 12) increase in size moving radially outward.
6. The turbine engine (20) of claim 1 , characterized in that the at least one combustor inlet static mixing system (100) is also formed from at least one radially inward extending static mixing arm (12) extending from an outer wall (32) toward an opposing inner wall (34) forming the at least one compressor exhaust plenum (18) and at least one radially outward extending static mixing arm (14) extending from the inner wall (34) toward the outer wall (32).
7. The turbine engine (20) of claim 6, characterized in that a first side (36) of the at least one radially inward extending static mixing arm (12) is nonparallel and nonorthogonal relative to a second side (38) on an opposite side of the at least one radially inward extending static mixing arm (12).
8. The turbine engine (20) of claim 7, characterized in that the first and second sides (38, 38) extend from a base (40) to a tip (42) and where the first and second sides (36, 38) are positioned such that the tip (42) of the at least one radially inward extending static mixing arm (12) has a width (44) that is narrower than a width (48) of the base (40) of the at least one radially inward extending static mixing arm (12),
9. The turbine engine (20) of claim 6, characterized in that a first side (48) of the at least one radially outward extending static mixing arm (14) is nonparallel and nonorthogonal relative to a second side (50) on an opposite side of the at least one radially outward extending static mixing arm (14).
10. The turbine engine (20) of claim 9, characterized in that the first and second sides (48, 50) extend from a base (56) to a tip (58) and where the first and second sides (48, 50) are positioned such that the tip (58) of the at least one radially outward extending static mixing arm (14) has a width (52) that is narrower than a width (54) of the base (58) of the at least one radially outward extending static mixing arm (14).
1 1. The turbine engine (20) of claim 6, characterized in that a tip (42) of the at least one radially inward extending static mixing arm (12) is positioned closer to the inner wall (34) from which the at least one radially outward extending static mixing arm (14) extends than a tip (58) of the at least one radially outward extending static mixing arm (14).
12. The turbine engine (20) of claim 6, characterized in that the at least one radially inward extending static mixing arm (12) is offset laterally relative to a longitudinal axis (60) of the at least one compressor exhaust plenum (18) from the at least one radially outward extending static mixing arm (14).
13. The turbine engine (20) of claim 6, wherein a first side (36) of the at least one radially inward extending static mixing arm (12) is aligned with a second side (38) of the at least one radially outward extending static mixing arm (14).
14. The turbine engine (20) of claim 6, characterized in that a cross-section of a flow path (62) established by the at least one compressor exhaust flow static mixing system (10) has a consistent width (64) when measured orthogonally from a surface forming one of the at least one radially inward extending static mixing arm (12), the at least one radially outward extending static mixing arm (14), the inner wall (34) and the outer wall (32).
15. The turbine engine (20) of claim 6, characterized in that the at least one radially inward extending static mixing arm (12) has a linear tip (42), and wherein the at least one radially outward extending static mixing arm (14) has a linear tip (58).
16. The turbine engine (20) of claim 6, characterized in that the at least one radially inward extending static mixing arm (12) is positioned in a portion of the at least one compressor exhaust plenum (18) that is formed at the inner wall (34) from a diffuser lip (68) and at the outer wall (32) from a combustor liner (70), and wherein the at least one compressor exhaust plenum (18) formed between the inner wall (34) formed from the diffuser lip (68) and the outer wall (32) formed from the combustor liner (70) is in the shape of an annu!us.
17. The turbine engine (20) of claim 1 , characterized in that the first and second circumferentiaiiy extending static mixing arms (1 10, 112) are nonorthogonal and nonparallel to a direction of flow such that the first and second circumferentiaiiy extending static mixing arms (1 10, 1 12) are angled in a downstream direction such that bases of the first and second circumferentiaiiy extending static mixing arms (110, 112) are positioned further upstream than tips (128, 130) of the first and second circumferentiaiiy extending static mixing arms (1 10, 1 12).
PCT/US2014/020692 2014-03-05 2014-03-05 Combustor inlet flow static mixing system for conditioning air being fed to the combustor in a gas turbine engine WO2015134010A1 (en)

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3460331A1 (en) * 2017-09-21 2019-03-27 General Electric Company Canted combustor for gas turbine engine

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2704089A (en) * 1952-06-09 1955-03-15 Lee R Woodworth Gas turbine diffuser
GB995244A (en) * 1961-06-01 1965-06-16 Bristol Siddeley Engines Ltd Variable spread fluid dispersal system
US4796429A (en) * 1976-11-15 1989-01-10 General Motors Corporation Combustor diffuser
US5513982A (en) * 1993-04-08 1996-05-07 Abb Management Ag Combustion chamber
WO1998028574A2 (en) * 1996-12-20 1998-07-02 Siemens Aktiengesellschaft Burner for liquid fuels, method of operating a burner, and swirling element
US20030110774A1 (en) * 2001-06-07 2003-06-19 Keijiro Saitoh Combustor
US20120024985A1 (en) * 2010-08-02 2012-02-02 General Electric Company Integrated fuel nozzle and inlet flow conditioner and related method
WO2014114533A1 (en) * 2013-01-24 2014-07-31 Siemens Aktiengesellschaft Burner system having turbulence elements

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2704089A (en) * 1952-06-09 1955-03-15 Lee R Woodworth Gas turbine diffuser
GB995244A (en) * 1961-06-01 1965-06-16 Bristol Siddeley Engines Ltd Variable spread fluid dispersal system
US4796429A (en) * 1976-11-15 1989-01-10 General Motors Corporation Combustor diffuser
US5513982A (en) * 1993-04-08 1996-05-07 Abb Management Ag Combustion chamber
WO1998028574A2 (en) * 1996-12-20 1998-07-02 Siemens Aktiengesellschaft Burner for liquid fuels, method of operating a burner, and swirling element
US20030110774A1 (en) * 2001-06-07 2003-06-19 Keijiro Saitoh Combustor
US20120024985A1 (en) * 2010-08-02 2012-02-02 General Electric Company Integrated fuel nozzle and inlet flow conditioner and related method
WO2014114533A1 (en) * 2013-01-24 2014-07-31 Siemens Aktiengesellschaft Burner system having turbulence elements

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3460331A1 (en) * 2017-09-21 2019-03-27 General Electric Company Canted combustor for gas turbine engine

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