US20150362189A1 - Burner system with resonator - Google Patents

Burner system with resonator Download PDF

Info

Publication number
US20150362189A1
US20150362189A1 US14/303,866 US201414303866A US2015362189A1 US 20150362189 A1 US20150362189 A1 US 20150362189A1 US 201414303866 A US201414303866 A US 201414303866A US 2015362189 A1 US2015362189 A1 US 2015362189A1
Authority
US
United States
Prior art keywords
resonator
burner
arrangement
burner arrangement
combustion chamber
Prior art date
Legal status (The legal status 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 status listed.)
Abandoned
Application number
US14/303,866
Inventor
Andreas Böttcher
Peter Kaufmann
Andre Kluge
Boris Ferdinand Kock
William R. Ryan
Udo Schmitz
Daniel Vogtmann
Jaap van Kampen
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
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 AG filed Critical Siemens AG
Priority to US14/303,866 priority Critical patent/US20150362189A1/en
Assigned to SIEMENS AKTIENGESELLSCHAFT reassignment SIEMENS AKTIENGESELLSCHAFT ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: BOTTCHER, ANDREAS, KAUFMANN, PETER, KLUGE, ANDRE, Kock, Boris Ferdinand, SCHMITZ, UDO, VAN KAMPEN, JAAP, VOGTMANN, DANIEL
Assigned to SIEMENS ENERGY, INC. reassignment SIEMENS ENERGY, INC. ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: RYAN, WILLIAM R
Assigned to SIEMENS AKTIENGESELLSCHAFT reassignment SIEMENS AKTIENGESELLSCHAFT ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: SIEMENS ENERGY, INC.
Priority to PCT/EP2015/062560 priority patent/WO2015189101A1/en
Publication of US20150362189A1 publication Critical patent/US20150362189A1/en
Abandoned legal-status Critical Current

Links

Images

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
    • F23R3/28—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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M20/00—Details of combustion chambers, not otherwise provided for, e.g. means for storing heat from flames
    • F23M20/005—Noise absorbing means
    • 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
    • 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
    • F23R3/34—Feeding into different combustion zones
    • F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion
    • 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
    • F23R2900/00014—Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators

Definitions

  • the present invention refers to a burner system comprising a pilot burner arrangement, a main burner arrangement surrounding the pilot burner arrangement, a combustion chamber arranged downstream with respect to the pilot burner arrangement and the main burner arrangement, and at least one resonator, wherein the main burner arrangement defines a ring-shaped air supply outwardly delimited by a burner cone and provided with radially extending swirl vanes.
  • the swirl vanes can be fixed to the burner cone.
  • Burner systems of the above-mentioned kind are used for firing fluidic fuels in order to operate a turbo-engine, such as a gas turbine.
  • a turbo-engine such as a gas turbine.
  • burner systems are prone to combustion dynamics, which may arise as a result of a flame excitation, aerodynamic induced excitation or insufficient damping.
  • the combustion dynamics may cause high acoustic noises as well as damages to components of the burner system.
  • it is known to perform acoustic damping of critical frequencies by means of resonators, which are, for example, directly fixed to the outer wall of the combustion chamber.
  • the present invention provides a burner system of the above-mentioned kind, which is characterized in that a resonator cavity of the at least one resonator is formed at the outside of the burner cone, wherein the resonator cavity is provided with a plurality of resonator openings defining a fluidic connection between the resonator cavity and the combustion chamber.
  • a resonator cavity of the at least one resonator is formed at the outside of the burner cone, wherein the resonator cavity is provided with a plurality of resonator openings defining a fluidic connection between the resonator cavity and the combustion chamber.
  • the resonator cavity is designed in the form of a ring.
  • the resonator cavity can be produced with a low number of parts.
  • the ring-shaped resonator cavity can be divided by walls into sections. Each section can comprise at least one of the resonator openings.
  • the resonator cavity is defined by at least one panel sheet fixed to the outside of the burner cone.
  • the outer wall of the burner cone forms a part of the resonator, which is advantageous with respect to the costs of manufacture.
  • the resonator openings are evenly spaced apart from each other.
  • the resonator openings are defined by tubes extending through a wall of the resonator cavity.
  • Such tubes are advantageous in that their length, their diameter and their installation positions can be easily adapted to the frequencies, which are to be damped by means of the resonator.
  • the resonator openings are directed towards the combustion chamber.
  • FIG. 1 is a schematic sectional view of a gas turbine according to the prior art
  • FIG. 2 is a schematic representation of a part of a burner system according to one embodiment of the present invention.
  • FIG. 3 is a perspective cross sectional view of the burner system shown in FIG. 1 .
  • FIG. 1 shows a schematic sectional view of a gas turbine 1 according to the prior art.
  • the gas turbine 100 has, in the interior, a rotor 300 which is mounted so as to be rotatable about an axis of rotation 200 and which has a shaft 400 , said rotor also being referred to as turbine rotor.
  • a rotor 300 Arranged in succession along the rotor 300 are an intake housing 600 , a compressor 800 , a combustion system 900 , a turbine 140 , and an exhaust housing 150 , the combustion system 900 having a number of combustors 100 which each comprise a burner arrangement 110 and a combustion chamber 120 .
  • the combustion system 900 communicates with a hot-gas duct, which is for example of annular form.
  • Each turbine stage is formed from rings of blades.
  • a row formed from guide blades 170 is followed by a row formed from rotor blades 180 .
  • the guide blades 170 are fastened to an inner housing of a stator 190
  • the rotor blades 180 of a row are for example attached via a turbine disk to the rotor 300 .
  • a generator (not illustrated), for example, is coupled to the rotor 300 .
  • air is drawn in through the intake housing 600 , and compressed, by the compressor 800 .
  • the compressed air L′′ that is provided at the turbine-side end of the compressor 800 is conducted via a burner plenum 700 to the combustion system 900 and, in the latter, is mixed with a fuel in the region of the burner arrangement 110 .
  • the mixture is burned so as to form a working gas stream in the combustion system 900 .
  • the working gas stream flows along the hot-gas duct past the guide blades 170 and the rotor blades 180 .
  • the working gas stream expands at the rotor blades 180 so as to impart an impetus thereto, such that the rotor blades 180 drive the rotor 300 , and said rotor drives the generator (not illustrated) that is coupled thereto.
  • FIGS. 2 and 3 show a burner system 1 according to an embodiment of the present invention.
  • the burner system 1 comprises a pilot burner arrangement 2 , a main burner arrangement 3 surrounding the pilot burner arrangement 2 and a combustion chamber (not shown) arranged downstream with respect to the pilot burner arrangement 2 and the main burner arrangement 3 .
  • the pilot burner arrangement 2 and the main burner arrangement are both designed to be operated with gaseous and/or liquid fuels.
  • the burner system 1 can also be configured to be operated merely with gaseous or merely with liquid fuels.
  • the pilot burner arrangement 2 comprises an oil supply 4 leading to an oil nozzle 5 facing towards the combustion chamber. Moreover, the pilot burner arrangement 2 has a gas supply 6 surrounding the oil supply 4 . The gas supply 6 is again surrounded by an air supply 7 provided with swirl vanes 8 in a known fashion.
  • the main burner arrangement 3 comprises a gas supply 9 leading to a ring-shaped gas chamber 10 , an oil supply 11 leading to a ring-shaped oil chamber 12 , and a ring-shaped air supply 13 outwardly delimited by a burner cone 14 and provided with radially extending swirl vanes 15 fixed to the burner cone 14 .
  • the swirl vanes 15 are provided with outlet nozzles 16 , which are connected to either the gas chamber 10 or the oil chamber 12 .
  • the burner cone 14 is provided with a resonator 17 .
  • the resonator 17 comprises a ring-shaped resonator cavity 18 , which is defined by a panel sheet 19 fixed to the outside of the burner cone 14 , and a plurality of resonator openings 20 defining a fluidic connection between the resonator cavity 18 and the combustion chamber.
  • the resonator openings 20 are formed by tubes 21 .
  • the tubes 21 extend through a wall of the resonator 17 , are arranged evenly spaced apart from each other along the perimeter of the resonator 17 and are directed towards the combustion chamber.
  • gas delivered by the gas supply 9 or oil delivered by the oil supply 11 is distributed within the ring-shaped gas chamber 10 or the ring-shaped oil chamber 12 and is injected in the airflow guided through the air supply 13 by means of the outlet nozzles 16 formed in the swirler vanes 15 .
  • the fuel-air-mixture is then discharged in the combustion chamber, where it is burned.
  • the pilot burner arrangement 2 stabilizes the combustion within the combustion chamber.
  • the combustion causes combustion dynamics, which can lead to high acoustic noises as well as to damages to components of the burner system 1 .
  • critical frequencies are damped by means of the resonator 17 .
  • the critical frequencies to be damped by the resonator 17 can be adjusted by means of an appropriate choice of the size of the resonator cavity 18 as well as of the length, diameter and position of the resonator openings 20 defined by the tubes 21 .

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)

Abstract

The present invention relates to a burner system (1) comprising a pilot burner arrangement (2), a main burner arrangement (3) surrounding the pilot burner arrangement (2), a combustion chamber arranged downstream with respect to the pilot burner arrangement (2) and the main burner arrangement (3), and at least one resonator (17), wherein the main burner arrangement (3) defines a ring-shaped air supply (13) outwardly delimited by a burner cone (14) and provided with radially extending swirl vanes (15), wherein a resonator cavity (18) of the at least one resonator (17) is formed at the outside of the burner cone (14), wherein the resonator cavity (18) is provided with a plurality of resonator openings (20) defining a fluidic connection between the resonator cavity (18) and the combustion chamber.

Description

  • The present invention refers to a burner system comprising a pilot burner arrangement, a main burner arrangement surrounding the pilot burner arrangement, a combustion chamber arranged downstream with respect to the pilot burner arrangement and the main burner arrangement, and at least one resonator, wherein the main burner arrangement defines a ring-shaped air supply outwardly delimited by a burner cone and provided with radially extending swirl vanes. The swirl vanes can be fixed to the burner cone.
  • Burner systems of the above-mentioned kind are used for firing fluidic fuels in order to operate a turbo-engine, such as a gas turbine. During operation burner systems are prone to combustion dynamics, which may arise as a result of a flame excitation, aerodynamic induced excitation or insufficient damping. The combustion dynamics may cause high acoustic noises as well as damages to components of the burner system. In order to solve this problem, it is known to perform acoustic damping of critical frequencies by means of resonators, which are, for example, directly fixed to the outer wall of the combustion chamber.
  • It is an object of the present invention to provide a burner system of the above-mentioned kind having an alternative structure.
  • In order to solve this object the present invention provides a burner system of the above-mentioned kind, which is characterized in that a resonator cavity of the at least one resonator is formed at the outside of the burner cone, wherein the resonator cavity is provided with a plurality of resonator openings defining a fluidic connection between the resonator cavity and the combustion chamber. Such an integral structure of the at least one resonator and the burner cone is advantageous in that the resonator only needs little installation space and can be produced at low costs. Moreover, the resonator is arranged immediately next to the combustion chamber. Accordingly, the critical frequencies can be damped right next to the place of origin.
  • Preferably the resonator cavity is designed in the form of a ring. Thus, the resonator cavity can be produced with a low number of parts. The ring-shaped resonator cavity can be divided by walls into sections. Each section can comprise at least one of the resonator openings.
  • According to one aspect of the present invention the resonator cavity is defined by at least one panel sheet fixed to the outside of the burner cone. Thus, the outer wall of the burner cone forms a part of the resonator, which is advantageous with respect to the costs of manufacture.
  • Preferably, the resonator openings are evenly spaced apart from each other.
  • According to one aspect of the present invention, the resonator openings are defined by tubes extending through a wall of the resonator cavity. Such tubes are advantageous in that their length, their diameter and their installation positions can be easily adapted to the frequencies, which are to be damped by means of the resonator.
  • Preferably, the resonator openings are directed towards the combustion chamber.
  • Further features and advantages of the present invention will become apparent by means of the following description of a burner system according to one embodiment of the present invention with reference to the accompanying drawing. In the drawing
  • FIG. 1 is a schematic sectional view of a gas turbine according to the prior art,
  • FIG. 2 is a schematic representation of a part of a burner system according to one embodiment of the present invention and
  • FIG. 3 is a perspective cross sectional view of the burner system shown in FIG. 1.
    •
  • The FIG. 1 shows a schematic sectional view of a gas turbine 1 according to the prior art. The gas turbine 100 has, in the interior, a rotor 300 which is mounted so as to be rotatable about an axis of rotation 200 and which has a shaft 400, said rotor also being referred to as turbine rotor. Arranged in succession along the rotor 300 are an intake housing 600, a compressor 800, a combustion system 900, a turbine 140, and an exhaust housing 150, the combustion system 900 having a number of combustors 100 which each comprise a burner arrangement 110 and a combustion chamber 120. The combustion system 900 communicates with a hot-gas duct, which is for example of annular form. There, multiple turbine stages positioned one behind the other form the turbine 140. Each turbine stage is formed from rings of blades. In the hot-gas duct, as viewed in the flow direction of a working medium, a row formed from guide blades 170 is followed by a row formed from rotor blades 180. Here, the guide blades 170 are fastened to an inner housing of a stator 190, whereas the rotor blades 180 of a row are for example attached via a turbine disk to the rotor 300. A generator (not illustrated), for example, is coupled to the rotor 300.
  • During the operation of the gas turbine, air is drawn in through the intake housing 600, and compressed, by the compressor 800. The compressed air L″ that is provided at the turbine-side end of the compressor 800 is conducted via a burner plenum 700 to the combustion system 900 and, in the latter, is mixed with a fuel in the region of the burner arrangement 110. Then, with the aid of the burner arrangement 110, the mixture is burned so as to form a working gas stream in the combustion system 900. From there, the working gas stream flows along the hot-gas duct past the guide blades 170 and the rotor blades 180. The working gas stream expands at the rotor blades 180 so as to impart an impetus thereto, such that the rotor blades 180 drive the rotor 300, and said rotor drives the generator (not illustrated) that is coupled thereto.
  • The FIGS. 2 and 3 show a burner system 1 according to an embodiment of the present invention. The burner system 1 comprises a pilot burner arrangement 2, a main burner arrangement 3 surrounding the pilot burner arrangement 2 and a combustion chamber (not shown) arranged downstream with respect to the pilot burner arrangement 2 and the main burner arrangement 3. The pilot burner arrangement 2 and the main burner arrangement are both designed to be operated with gaseous and/or liquid fuels. However, it should be noted, that the burner system 1 can also be configured to be operated merely with gaseous or merely with liquid fuels.
  • The pilot burner arrangement 2 comprises an oil supply 4 leading to an oil nozzle 5 facing towards the combustion chamber. Moreover, the pilot burner arrangement 2 has a gas supply 6 surrounding the oil supply 4. The gas supply 6 is again surrounded by an air supply 7 provided with swirl vanes 8 in a known fashion.
  • The main burner arrangement 3 comprises a gas supply 9 leading to a ring-shaped gas chamber 10, an oil supply 11 leading to a ring-shaped oil chamber 12, and a ring-shaped air supply 13 outwardly delimited by a burner cone 14 and provided with radially extending swirl vanes 15 fixed to the burner cone 14. The swirl vanes 15 are provided with outlet nozzles 16, which are connected to either the gas chamber 10 or the oil chamber 12. The burner cone 14 is provided with a resonator 17. The resonator 17 comprises a ring-shaped resonator cavity 18, which is defined by a panel sheet 19 fixed to the outside of the burner cone 14, and a plurality of resonator openings 20 defining a fluidic connection between the resonator cavity 18 and the combustion chamber. The resonator openings 20 are formed by tubes 21. The tubes 21 extend through a wall of the resonator 17, are arranged evenly spaced apart from each other along the perimeter of the resonator 17 and are directed towards the combustion chamber.
  • During the operation of the burner system 1 gas delivered by the gas supply 9 or oil delivered by the oil supply 11 is distributed within the ring-shaped gas chamber 10 or the ring-shaped oil chamber 12 and is injected in the airflow guided through the air supply 13 by means of the outlet nozzles 16 formed in the swirler vanes 15. The fuel-air-mixture is then discharged in the combustion chamber, where it is burned. The pilot burner arrangement 2 stabilizes the combustion within the combustion chamber. The combustion causes combustion dynamics, which can lead to high acoustic noises as well as to damages to components of the burner system 1. In order to eliminate dangerous combustion dynamics, critical frequencies are damped by means of the resonator 17. The critical frequencies to be damped by the resonator 17 can be adjusted by means of an appropriate choice of the size of the resonator cavity 18 as well as of the length, diameter and position of the resonator openings 20 defined by the tubes 21.
  • Even though the present invention was described herein by means of a detailed embodiment, it should be noticed that the present invention is not limited by the embodiment. It is rather possible for a skilled person to derive modifications and variations from the embodiment without leaving the scope of protection defined in the accompanying claims.

Claims (6)

1. Burner system comprising a pilot burner arrangement, a main burner arrangement surrounding the pilot burner arrangement, a combustion chamber arranged downstream with respect to the pilot burner arrangement and the main burner arrangement, and at least one resonator, wherein the main burner arrangement defines a ring-shaped air supply outwardly delimited by a burner cone and provided with radially extending swirl vanes, wherein a resonator cavity of the at least one resonator is formed at the outside of the burner cone, wherein the resonator cavity is provided with a plurality of resonator openings defining a fluidic connection between the resonator cavity and the combustion chamber.
2. Burner system according to claim 1, wherein said resonator cavity is designed in the form of a ring.
3. Burner system according to claim 1, wherein said resonator cavity is defined by at least one panel sheet fixed to the outside of the burner cone.
4. Burner system according to claim 1, claim 1 said resonator openings are evenly spaced apart from each other.
5. Burner system according to claim 1, wherein said resonator openings are defined by tubes extending through a wall of the resonator.
6. Burner system according to claim 1, wherein said resonator openings are directed towards said combustion chamber.
US14/303,866 2014-06-13 2014-06-13 Burner system with resonator Abandoned US20150362189A1 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
US14/303,866 US20150362189A1 (en) 2014-06-13 2014-06-13 Burner system with resonator
PCT/EP2015/062560 WO2015189101A1 (en) 2014-06-13 2015-06-05 Burner system with resonator

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US14/303,866 US20150362189A1 (en) 2014-06-13 2014-06-13 Burner system with resonator

Publications (1)

Publication Number Publication Date
US20150362189A1 true US20150362189A1 (en) 2015-12-17

Family

ID=53442736

Family Applications (1)

Application Number Title Priority Date Filing Date
US14/303,866 Abandoned US20150362189A1 (en) 2014-06-13 2014-06-13 Burner system with resonator

Country Status (2)

Country Link
US (1) US20150362189A1 (en)
WO (1) WO2015189101A1 (en)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106801891B (en) * 2017-01-20 2019-11-12 南京航空航天大学 A kind of fuel-rich and punching press combination gas generator for superb energy resource system

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1342952A1 (en) * 2002-03-07 2003-09-10 Siemens Aktiengesellschaft Burner, process for operating a burner and gas turbine
EP1342953A1 (en) * 2002-03-07 2003-09-10 Siemens Aktiengesellschaft Gas turbine
US8127546B2 (en) * 2007-05-31 2012-03-06 Solar Turbines Inc. Turbine engine fuel injector with helmholtz resonators
ITMI20122265A1 (en) * 2012-12-28 2014-06-29 Ansaldo Energia Spa BURNER GROUP FOR A GAS TURBINE PROVIDED WITH A HELMHOLTZ RESONATOR

Also Published As

Publication number Publication date
WO2015189101A1 (en) 2015-12-17

Similar Documents

Publication Publication Date Title
US8904798B2 (en) Combustor
JP5947515B2 (en) Turbomachine with mixing tube element with vortex generator
US9217373B2 (en) Fuel nozzle for reducing modal coupling of combustion dynamics
US20220026068A1 (en) Fuel nozzle for gas turbine engine combustor
US10215415B2 (en) Premix fuel nozzle assembly cartridge
TWI576509B (en) Nozzle, combustor, and gas turbine
JP2010210229A (en) Injection device for turbomachine
EP2806217B1 (en) Gas turbine engines with fuel injector assemblies
CN113483355B (en) Reflow-combustion liner, reflow-combustor, and method of mixing cooling air therein
JP2007292075A (en) Optimized configuration of reverse flow combustion system of gas turbine engine
CN109563995B (en) Fuel-air mixer assembly for use in a combustor of a turbine engine
US9322553B2 (en) Wake manipulating structure for a turbine system
JP2010175243A (en) System and method for reducing combustion dynamics in turbomachine
US9546600B2 (en) Nozzle having an orifice plug for a gas turbomachine
JP2011141111A (en) Turbomachine nozzle
US11060726B2 (en) Compressor diffuser and gas turbine
CN107850308B (en) Combustor for gas turbine
US20150362189A1 (en) Burner system with resonator
JP2019056548A (en) Non-uniform mixer for combustion dynamics attenuation
US20190056109A1 (en) Main fuel nozzle for combustion dynamics attenuation
US11994295B2 (en) Multi pressure drop swirler ferrule plate
EP4206534A1 (en) Turbine engine fuel premixer
CN116293791A (en) Burner with resonator

Legal Events

Date Code Title Description
AS Assignment

Owner name: SIEMENS AKTIENGESELLSCHAFT, GERMANY

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:BOTTCHER, ANDREAS;KAUFMANN, PETER;KLUGE, ANDRE;AND OTHERS;SIGNING DATES FROM 20140627 TO 20140707;REEL/FRAME:033559/0522

Owner name: SIEMENS ENERGY, INC., FLORIDA

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:RYAN, WILLIAM R;REEL/FRAME:033559/0644

Effective date: 20140725

Owner name: SIEMENS AKTIENGESELLSCHAFT, GERMANY

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:SIEMENS ENERGY, INC.;REEL/FRAME:033559/0788

Effective date: 20140801

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION