EP3134677B1 - Brenner mit fluidischem oszillator, für eine gasturbine und gasturbine mit mindestens einem derartigen brenner - Google Patents

Brenner mit fluidischem oszillator, für eine gasturbine und gasturbine mit mindestens einem derartigen brenner Download PDF

Info

Publication number: EP3134677B1
Authority: EP; European Patent Office
Prior art keywords: fuel; burner; interaction chamber; region; output
Prior art date: 2014-09-12
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.): Not-in-force

Application number

EP15763533.5A

Other languages

German (de)

English (en)

French (fr)

Other versions

EP3134677A1 (de

Inventor

Andreas Böttcher

Olga Deiss

Thomas Grieb

Matthias Hase

Werner Krebs

Patrick Lapp

Sebastian Pfadler

Daniel Vogtmann

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.)

2014-09-12

Filing date

2015-09-07

Publication date

2018-03-07

2015-09-07 Application filed by Siemens AG filed Critical Siemens AG

2017-03-01 Publication of EP3134677A1 publication Critical patent/EP3134677A1/de

2018-03-07 Application granted granted Critical

2018-03-07 Publication of EP3134677B1 publication Critical patent/EP3134677B1/de

Status Not-in-force legal-status Critical Current

2035-09-07 Anticipated expiration legal-status Critical

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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
- F23D—BURNERS
- F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
- F23D11/36—Details, e.g. burner cooling means, noise reduction 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
- F23R3/02—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
- F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
- F23R3/20—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants incorporating fuel injection means
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN A CARRIER GAS OR AIR
- F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
- F23C2900/07001—Air swirling vanes incorporating fuel injectors
- 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 invention relates to a burner for a gas turbine with a central burner axis and a burner axis at least partially surrounding Vormischpassage.
the premix passage thus has a passage cross-sectional area which extends around the burner axis.
the central burner axis is an imaginary, infinitely long line.
the passage cross-sectional area can be arranged, for example, annularly or as a full circle around the burner axis.
the premix passage can run coaxially (same axis of rotation) to the burner axis.
the diameter of the ring or full circle may vary along the burner axis section.
the premix passage can be formed, at least in sections, as a ring-chamber passage (annular cross-section), which can transition into a premix passage section, which is designed as a full circle in cross-section.
the premix passage is bounded radially outwardly by a wall.
the premix passage can be flowed through during operation of compressor air. It serves to mix fuel and air, wherein a burner lance or burner hub and a number of fuel injectors are arranged in the premix passage.
the fuel injectors extending from the burner lance / hub toward the wall are fluidly coupled to fuel nozzles that are at least partially connected to the fuel lance hub / hub.
the fuel injectors may include both gaseous fuel fuel nozzles and fuel nozzles for oil operation. The same applies to the burner lance / hub, which may alternatively be formed without fuel nozzles.
the burner lance can also be called a burner hub in the context of this invention.
the burner lance can be arranged centrally in the premix passage.
the burner lance can protrude from upstream into the premix passage, so that the passage is limited only in sections radially inward from the burner lance.
the premix passage may have a full circular cross-sectional area downstream of the burner lance.
the burner lance may also extend substantially to the exit of the premix passage.
the premix passage may be bounded radially inward at least in sections by a burner hub with a substantially truncated cone-shaped surface arranged centrally in the passage, which bounds the premix passage radially to the inside from an upstream end to an end region of the hub.
the Vormischpassage can go downstream of the hub in a full-circle in cross-section Vormisch Scheme.
the premix passage thus has an annular passage cross-sectional area whose diameter may decrease in the flow direction.
further premix passages may be arranged in the burner hub or, for example, a central pilot burner.
the premix passage may also be referred to as premix channel in the context of this invention.
Fuel is injected into the premix passage via the fuel injectors and may mix with a compressor airflow flowing through the premix passage to the downstream exit of the premix passage so that the premix burner provides at its exit a fuel / air mixture for discharge into a combustion chamber.
fuel can also be injected via fuel nozzles arranged directly on the burner lance
Object of the present invention is to provide a burner of the type mentioned for a gas turbine, with which in the operation of the burner, a reduction of pollutant emissions or a reduction of pressure pulsations is possible.
the fuel supply arrangement comprises at least one fluidic oscillator with an interaction chamber, wherein an input of the interaction chamber is connected to a fuel passage of the fuel supply arrangement and a first output channel of the interaction chamber is at least up to a first Fuel nozzle extends and a second output channel extends at least to a second fuel nozzle, wherein the fluidic oscillator per output channel comprises a feedback line, wherein the feedback line opens with its one end in the region downstream of the at least one fuel nozzle in the respective output channel and the other end into an entrance area of the interaction chamber.
the at least first and the at least second fuel nozzle or the first and second group of fuel nozzles can be arranged on a common fuel injector and distributed in the radial direction for a homogeneous distribution of the fuel in the premix passage.
the at least first fuel nozzle could, for example, also be arranged on a suction side and the at least second fuel nozzle on a pressure side of a bucket-type fuel injector be.
the first and second groups of fuel nozzles can also be arranged, for example, on different fuel injectors. For example, in fuel injectors arranged substantially opposite to the burner lance.
Fluidic oscillators have long been known as fluidic controls that do without expensive valves. For example, these are used for the supply of air in the boundary layer of wings to prevent separation of the boundary layer.
Fluidic oscillators in the field of fuel injection in gas turbine combustion chambers are, for example, from the documents US 20110023493 and US 3748852 known.
the feedback signal is lower and the fuel will flow longer in the output channel than in reverse pressure conditions before the fuel nozzles of the output channel in the premix passage. If the static pressure in the premix passage in the area of a fuel nozzle group is lower, more fuel flows through the associated outlet channel when the associated output of the interaction chamber is pressurized, and the dynamic pressure in the output channel is higher.
the associated feedback line opens into the exit channel downstream of the at least one fuel nozzle of the exit channel
the pressure in the feedback line opening into the end region of the exit channel is higher and the associated fuel jet will more rapidly detach from the sidewall in the entrance area of the interaction chamber and fuel the next exit apply.
the oscillation of the fuel jet in the interaction chamber will supply the output channel with fuel for a longer period of time a fuel nozzle opens into a region of the premix passage in which a higher pressure prevails. This compensates for the effect that in general less fuel escapes from fuel nozzles, which discharge into a region of higher passenger pressure or more fuel is injected into regions of low pressure. By means of this compensation, a more homogeneous fuel concentration can be generated in the premix passage according to the invention.
the injection of the fuel through the at least two fuel nozzle groups or fuel nozzles connected to the fluidic oscillator regulates independently, without the need for an additional control device.
the resulting more homogeneous distribution of fuel concentration in the premix passage leads to reduced pollutant emissions.
Due to the temporally and locally fluctuating fuel injection a good mixing of the fuel, which is spouted out by the fuel nozzle groups, with the compressor air flowing past is also brought about.
a broadening of the delay time profile of the burner is effected, whereby an interaction of the burner with the flame and an increase of thermoacoustic vibrations is reduced.
the supplied through the fluidic oscillator fuel nozzle or fuel nozzle groups of the burner due to the both temporally and locally pulsating fuel jet at the outlet of the nozzles conditionally a fluctuation of the fuel concentration profile in the passing compressor air, which in turn the thermoacoustic stability due to a broadened delay time profile the burner improved - for example, compared to burners with conventional pressure-swirl nozzles or full-jet nozzles.
a frequency of the pulsating injection of the fuel can be adjusted for example by the size of the interaction chamber.
the burner may include a plurality of fluidic oscillators, which supply at least two output channels each having at least one fuel nozzle or group of fuel nozzles with fuel.
the first output channel extends up to a first group of fuel nozzles and the second output channel extends up to a second group of fuel nozzles, wherein the feedback line respectively opens into an area downstream of the respective group of fuel nozzles in the output channel.
the at least two fuel nozzles or at least two fuel nozzle groups are arranged in a common fuel injector and differ in their radial arrangement in the Vormischpassage, so that the fuel concentration in the radial direction despite different pressure conditions in the burner near the lance and brennerlanzenfernen Uniform area of the premix passage.
the fluidic oscillator can be arranged in the burner hub or in the fuel injector.
the burner comprises more than two groups of fuel nozzles in different fuel injectors connected in such a way to the fluidic oscillator.
a further advantageous embodiment of the invention can provide that the different fuel injectors are arranged circumferentially on the burner lance and the associated output channels circumferentially on the interaction chamber.
the oscillation of a fuel jet entering the interaction chamber through the inlet under pressure is, according to this embodiment of the invention, ignited by alternately applying the jet to the divergently formed jet Sidewall portions.
the excitation of the oscillation in the interaction chamber according to the invention is based on the flow delay caused in the entrance area by the diverging side walls / sidewall regions.
the burner may be a centrally located pilot burner of the burner assembly.
the main burner of the burner assembly according to one of claims 1 to 11 may be formed.

Landscapes

Engineering & Computer Science (AREA)
Chemical & Material Sciences (AREA)
Combustion & Propulsion (AREA)
Mechanical Engineering (AREA)
General Engineering & Computer Science (AREA)
Gas Burners (AREA)
Nozzles For Spraying Of Liquid Fuel (AREA)
Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
Pre-Mixing And Non-Premixing Gas Burner (AREA)

EP15763533.5A 2014-09-12 2015-09-07 Brenner mit fluidischem oszillator, für eine gasturbine und gasturbine mit mindestens einem derartigen brenner Not-in-force EP3134677B1 (de)

Applications Claiming Priority (2)

Application Number	Priority Date	Filing Date	Title
DE102014218288		2014-09-12
PCT/EP2015/070355 WO2016037966A1 (de)	2014-09-12	2015-09-07	Brenner mit fluidischem oszillator, für eine gasturbine und gasturbine mit mindestens einem derartigen brenner

Publications (2)

Publication Number	Publication Date
EP3134677A1 EP3134677A1 (de)	2017-03-01
EP3134677B1 true EP3134677B1 (de)	2018-03-07

Family

ID=54140423

Family Applications (1)

Application Number	Title	Priority Date	Filing Date
EP15763533.5A Not-in-force EP3134677B1 (de)	2014-09-12	2015-09-07	Brenner mit fluidischem oszillator, für eine gasturbine und gasturbine mit mindestens einem derartigen brenner

Country Status (5)

Country	Link
US (1)	US20170254541A1 (zh)
EP (1)	EP3134677B1 (zh)
JP (1)	JP6321282B2 (zh)
CN (1)	CN106662328A (zh)
WO (1)	WO2016037966A1 (zh)

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EP3062019B1 (en) *	2015-02-27	2018-11-21	Ansaldo Energia Switzerland AG	Method and device for flame stabilization in a burner system of a stationary combustion engine
US10386074B2 (en) *	2016-12-09	2019-08-20	Solar Turbines Incorporated	Injector head with a resonator for a gas turbine engine
US11156162B2 (en) *	2018-05-23	2021-10-26	General Electric Company	Fluid manifold damper for gas turbine engine
KR102142140B1 (ko) *	2018-09-17	2020-08-06	두산중공업 주식회사	연료 노즐, 이를 포함하는 연소기 및 가스 터빈
US11156164B2 (en)	2019-05-21	2021-10-26	General Electric Company	System and method for high frequency accoustic dampers with caps
US11174792B2 (en)	2019-05-21	2021-11-16	General Electric Company	System and method for high frequency acoustic dampers with baffles
CN110449309B (zh) *	2019-08-16	2020-06-26	中国航空发动机研究院	一种流体振荡器阵列及其频率同步方法
CN113280366B (zh)	2021-05-13	2022-09-27	中国航空发动机研究院	一种基于自激扫掠振荡燃油喷嘴的加力燃烧室结构
CN114856827B (zh) *	2022-05-12	2023-06-30	中国航发四川燃气涡轮研究院	可调节喷嘴位置及喷射方向的可拆卸扇形喷嘴
KR20240003230A (ko) *	2022-06-30	2024-01-08	두산에너빌리티 주식회사	제트 노즐, 연소기 및 이를 포함하는 가스터빈

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US3748852A (en) *	1969-12-05	1973-07-31	L Cole	Self-stabilizing pressure compensated injector
US5456594A (en) *	1994-03-14	1995-10-10	The Boc Group, Inc.	Pulsating combustion method and apparatus
JP3457907B2 (ja) *	1998-12-24	2003-10-20	三菱重工業株式会社	デュアルフュエルノズル
JP2003148710A (ja) *	2001-11-14	2003-05-21	Mitsubishi Heavy Ind Ltd	燃焼器
US6718889B1 (en) *	2002-08-30	2004-04-13	Central Boiler, Inc.	Draft controlled boiler fuel nozzle
US6820431B2 (en) *	2002-10-31	2004-11-23	General Electric Company	Acoustic impedance-matched fuel nozzle device and tunable fuel injection resonator assembly
EP1662202B1 (de) *	2004-11-30	2016-11-16	Siemens Aktiengesellschaft	Brenner für eine Gasturbinenanlage
US8474265B2 (en) *	2009-07-29	2013-07-02	General Electric Company	Fuel nozzle for a turbine combustor, and methods of forming same
EP2327933A1 (de) *	2009-11-30	2011-06-01	Siemens Aktiengesellschaft	Brenneranordnung
US20110173983A1 (en) *	2010-01-15	2011-07-21	General Electric Company	Premix fuel nozzle internal flow path enhancement
US20110225973A1 (en) *	2010-03-18	2011-09-22	General Electric Company	Combustor with Pre-Mixing Primary Fuel-Nozzle Assembly
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2015
- 2015-09-07 US US15/503,990 patent/US20170254541A1/en not_active Abandoned
- 2015-09-07 WO PCT/EP2015/070355 patent/WO2016037966A1/de active Application Filing
- 2015-09-07 JP JP2017504403A patent/JP6321282B2/ja active Active
- 2015-09-07 CN CN201580033859.5A patent/CN106662328A/zh active Pending
- 2015-09-07 EP EP15763533.5A patent/EP3134677B1/de not_active Not-in-force

Also Published As

Publication number	Publication date
US20170254541A1 (en)	2017-09-07
JP2017527765A (ja)	2017-09-21
CN106662328A (zh)	2017-05-10
JP6321282B2 (ja)	2018-05-09
EP3134677A1 (de)	2017-03-01
WO2016037966A1 (de)	2016-03-17

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