EP2059724A1 - Chambre de combustion de turbine à gaz - Google Patents

Chambre de combustion de turbine à gaz

Info

Publication number
EP2059724A1
EP2059724A1 EP07818048A EP07818048A EP2059724A1 EP 2059724 A1 EP2059724 A1 EP 2059724A1 EP 07818048 A EP07818048 A EP 07818048A EP 07818048 A EP07818048 A EP 07818048A EP 2059724 A1 EP2059724 A1 EP 2059724A1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
zone
flame tube
post
primary combustion
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.)
Ceased
Application number
EP07818048A
Other languages
German (de)
English (en)
Inventor
Rainer Brinkmann
Holger Huitenga
Eric Norster
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.)
MAN Energy Solutions SE
Original Assignee
MAN Turbo 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 MAN Turbo AG filed Critical MAN Turbo AG
Publication of EP2059724A1 publication Critical patent/EP2059724A1/fr
Ceased legal-status Critical Current

Links

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
    • F23R3/002—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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/06—Arrangement of apertures along the flame tube
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03044—Impingement cooled combustion chamber walls or subassemblies

Definitions

  • the present invention relates to a combustion chamber intended in particular for use in a gas turbine. More specifically, the present invention relates to the air guidance of the compressed air supplied to the combustion chamber.
  • the typical structure of a gas turbine consisting of a compressor region, a combustion chamber region and a turbine region is well known and will not be explained in more detail below.
  • the compressed air that is supplied to the combustion chamber is introduced into the combustion process in a flame tube and also used for cooling the combustion chamber.
  • research and development in the field of gas turbines is aimed at continually reducing pollutant emissions from gas turbines.
  • the focus is on the pollutants NO x , CO 2 and CO and unburned hydrocarbons.
  • the pollutants in the combustion process of a gas turbine for example, by a lean mixture of the fuel-air mixture, ie more compressed air must be added to the fuel-air mixture, or can be achieved by optimal temperature distribution in the flame tube.
  • EP 0 732 546 B1 discloses a construction of the prior art to meet these requirements.
  • the compressed air which is supplied to the combustion chamber from the compressor region of the gas turbine is divided into two partial streams.
  • a partial flow is used for combustion in the flame tube, another the cooling of the outer wall of the combustion chamber, wherein the cooling air then enters the post-primary combustion zone.
  • a disadvantage of this structure is that only a predetermined proportion of the compressed air flow is ready for cooling. In other words, the lower the pollutant a gas turbine is designed, the less cooling air is available. Consequently, the efficiency of the gas turbine in favor of lower pollutant emissions must remain low.
  • the prior art according to EP 0 896 193 B1 has the disadvantage that no direct cooling in the flame tube interior can be provided by openings in the wall in the region of the post-primary combustion zone or secondary zone. This prior art thus does not achieve optimal cooling performance and is limited in the operation of the gas turbine.
  • the invention provides a combustion chamber for a gas turbine.
  • the flame tube of the combustion chamber is in the flow direction at least in a mixing zone for mixing a fuel with air to a fuel-air mixture, and a primary combustion zone or primary zone and a post-primary combustion zone or secondary zone.
  • a mixing zone for mixing a fuel with air to a fuel-air mixture
  • a primary combustion zone or primary zone and a post-primary combustion zone or secondary zone In the region of the mixing zone, which is formed in the vicinity of the burner, at least one opening is generally provided via channels of the burner into the interior of the flame tube.
  • the so-called mixing opening is likewise provided. This at least one opening or mixing opening serves to cool the combustion process.
  • About the openings mentioned compressed air which is previously compressed in the compression region of the gas turbine, enters the flame tube. The compressed air is provided for the cooling of the flame tube and passes through the openings described proportionally in the mixing zone and in the post-primary combustion zone.
  • the air for combustion at a higher temperature in the burner of the combustion chamber passes. Since the combustion temperature is raised in this way, the gas turbine can be operated with less fuel and still achieve the same temperature. This measure thus increases the efficiency of the gas turbine.
  • the new arrangement also allows the combustion gases in the post-primary combustion zone to be cooled.
  • the supply of air to the combustion process can be made variable, since theoretically all the compressed air could be fed into the combustion process.
  • the figure shows a schematic cross-sectional view of a combustion chamber according to the invention.
  • Reference numeral 1 shows a combustion chamber according to the embodiment with a flame tube 3 and a baffle 2 arranged radially outside the flame tube.
  • the combustion chamber 1 is part of a gas turbine (not shown) which is operated with gas and / or liquid fuel.
  • the flame tube is widely Cylindrical design. Compressed air flows through a compressor air duct onto the impact grille. Through the openings 4 of the baffle, the compressed air flowing from a compressor, or from the compressor region of the gas turbine to the combustion chamber, divided into numerous individual flows.
  • the openings 4 of the impact grid are formed as nozzles, so that the inflowing compressed air impinges jet-shaped.
  • the arrangement and geometry of the openings 4 of the impact grille can be adjusted so that the desired cooling performance is achieved on the surface of the flame tube.
  • the distribution of the impact cooling in the air portion 11 and the air portion 12 is designed adjustable. In this embodiment, this is achieved by changing the geometry of the openings 5 to the post-primary combustion zone 18 during operation. By cooling the flame tube 3, the service life of the machine elements used is increased and at the same time the air of the flow rate of the burner 11, 13 and the flow rate mixing port 12 is heated.
  • the impact grille is formed in this embodiment as a perforated plate which surrounds the flame tube (3) in the circumferential direction. Since the compressed air is not only passed along the outer wall of the flame tube 3, but with increased speed, preferably triggered by the nozzle action of the openings of the perforated plate 2, divided into numerous individual flows impinges on the outer surface of the flame tube, the cooling capacity is significantly increased.
  • the flow of compressed air directed to the flame tube 3 may also be angular, e.g. do not impinge perpendicular to the flame tube 3.
  • a device for dividing the directed to the flame tube 3 flow compressed air can preferably be provided in the compressor air passage 9.
  • this embodiment of the invention is also open to understand in which zones of the flame tube is cooled by impingement air.
  • 1 shows an embodiment in which both the pre- and post-primary burns cooling zone is cooled by impingement air.
  • the present invention is not limited to the impingement cooling with individual flows 10 striking the flame tube 3 substantially perpendicular or at an angle. Rather, a laminar flow along the outer wall of the flame tube 3 can provide the desired cooling performance. It is essential to the invention, in the first place, that the air used for cooling reaches the flame tube 3 both via the mixing openings 5 and via the openings 6. In addition, a combination of the described flow types for the cooling of the flame tube 3 as well as support by other cooling methods known in the art is conceivable.
  • the thus preheated air passes through the air duct 6 in the burner 7. There, the air is premixed with the fuel, which flows substantially along the fuel flow. Because the temperature of the fuel-air mixture is increased due to the preheated air used for the cooling of the flame tube compared to conventional fuel-air mixtures, the gas turbine with reduced fuel consumption can reach the same temperature as known from the prior art gas turbines.
  • the supplied compressed air is used substantially completely for the cooling of the fire tube 3 and divided into a flow portion 11, 13 to the opening 6 of the mixing zone 15 and a flow portion 12 to the opening 5 of the post-primary combustion zone 18.
  • the Mischö Stamms- flow 14 then flows through a plurality of mixing openings 5 substantially perpendicular to the fuel flow 8 in the flame tube 5.
  • the flow can be carried out by the mixing openings 5 and / or through the opening 6 to the mixing zone 15 controllable or adjustable. This can be done, for example, by changing the flow cross-section through said openings, but also by all other measures known to those skilled in the art. LIST OF REFERENCE NUMBERS

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

Chambre de combustion (1) pour une turbine à gaz. Un tube de flammes (3) de la chambre de combustion (1) présente, dans la direction d'écoulement, une zone de mélangeage (15) pour mélanger un combustible à de l'air afin de former un mélange combustible-air, une zone de combustion primaire (17) et une zone de combustion secondaire (18). Au moins une ouverture respective (5, 6) est prévue dans la région de la zone de mélangeage (15) et dans la région de la zone de combustion secondaire (18), afin de diriger de l'air comprimé dans le tube de flammes (3). L'air comprimé apporté est prévu pour refroidir le tube de flammes (3) et parvient ensuite, via les ouvertures (5, 6) dans la région de la zone de mélangeage (15) et dans la région de la zone de combustion secondaire (18), au prorata de ces ouvertures dans la zone de mélangeage (15) et dans la zone de combustion secondaire (18).
EP07818048A 2006-09-07 2007-09-04 Chambre de combustion de turbine à gaz Ceased EP2059724A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102006042124A DE102006042124B4 (de) 2006-09-07 2006-09-07 Gasturbinenbrennkammer
PCT/EP2007/007696 WO2008028621A1 (fr) 2006-09-07 2007-09-04 Chambre de combustion de turbine à gaz

Publications (1)

Publication Number Publication Date
EP2059724A1 true EP2059724A1 (fr) 2009-05-20

Family

ID=38982562

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07818048A Ceased EP2059724A1 (fr) 2006-09-07 2007-09-04 Chambre de combustion de turbine à gaz

Country Status (8)

Country Link
US (1) US20100126174A1 (fr)
EP (1) EP2059724A1 (fr)
JP (1) JP2010502928A (fr)
CN (1) CN101573560A (fr)
CA (1) CA2662720A1 (fr)
DE (1) DE102006042124B4 (fr)
RU (1) RU2009112629A (fr)
WO (1) WO2008028621A1 (fr)

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US7617684B2 (en) * 2007-11-13 2009-11-17 Opra Technologies B.V. Impingement cooled can combustor
DE102009035550A1 (de) * 2009-07-31 2011-02-03 Man Diesel & Turbo Se Gasturbinenbrennkammer
EP2405200A1 (fr) * 2010-07-05 2012-01-11 Siemens Aktiengesellschaft Appareil de combustion et moteur de turbine à gaz
NL2005381C2 (en) 2010-09-21 2012-03-28 Micro Turbine Technology B V Combustor with a single limited fuel-air mixing burner and recuperated micro gas turbine.
US9423132B2 (en) * 2010-11-09 2016-08-23 Opra Technologies B.V. Ultra low emissions gas turbine combustor
US9625153B2 (en) * 2010-11-09 2017-04-18 Opra Technologies B.V. Low calorific fuel combustor for gas turbine
US8844260B2 (en) * 2010-11-09 2014-09-30 Opra Technologies B.V. Low calorific fuel combustor for gas turbine
DE102011007562A1 (de) * 2011-04-18 2012-10-18 Man Diesel & Turbo Se Brennkammergehäuse und damit ausgerüstete Gasturbine
US9328663B2 (en) 2013-05-30 2016-05-03 General Electric Company Gas turbine engine and method of operating thereof
US9366184B2 (en) 2013-06-18 2016-06-14 General Electric Company Gas turbine engine and method of operating thereof
DE102014204482A1 (de) 2014-03-11 2015-09-17 Rolls-Royce Deutschland Ltd & Co Kg Brennkammer einer Gasturbine
EP2952812B1 (fr) * 2014-06-05 2018-08-08 General Electric Technology GmbH Chambre de combustion annulaire d'une turbine á gaz et segment de manchon
US11022313B2 (en) 2016-06-22 2021-06-01 General Electric Company Combustor assembly for a turbine engine
US10337738B2 (en) 2016-06-22 2019-07-02 General Electric Company Combustor assembly for a turbine engine
CN107101224B (zh) * 2017-05-23 2023-01-10 新奥能源动力科技（上海）有限公司 一种单管燃烧室和燃气轮机
DE102017125051A1 (de) 2017-10-26 2019-05-02 Man Diesel & Turbo Se Strömungsmaschine
DE102018125698A1 (de) 2018-10-17 2020-04-23 Man Energy Solutions Se Gasturbinenbrennkammer
US11181269B2 (en) 2018-11-15 2021-11-23 General Electric Company Involute trapped vortex combustor assembly
CN110657450B (zh) * 2019-10-31 2023-09-15 中国华能集团有限公司 一种燃气轮机的燃烧室及其工作方法
CN110848030B (zh) * 2019-11-25 2021-09-21 东方电气集团东方汽轮机有限公司 一种燃气轮机燃烧室火焰筒冲击冷却系统优化方法
CN113701195A (zh) * 2021-09-03 2021-11-26 永旭腾风新能源动力科技（北京）有限公司 双燃料管燃烧室及燃气轮机

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Also Published As

Publication number Publication date
WO2008028621A1 (fr) 2008-03-13
CN101573560A (zh) 2009-11-04
CA2662720A1 (fr) 2008-03-13
US20100126174A1 (en) 2010-05-27
DE102006042124A1 (de) 2008-03-27
JP2010502928A (ja) 2010-01-28
DE102006042124B4 (de) 2010-04-22
RU2009112629A (ru) 2010-10-20

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