EP2693124A1 - Pilotbrenner, Brenner, Brennkammer und Gasturbinenmotor - Google Patents

Pilotbrenner, Brenner, Brennkammer und Gasturbinenmotor Download PDF

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Publication number
EP2693124A1
EP2693124A1 EP12179053.9A EP12179053A EP2693124A1 EP 2693124 A1 EP2693124 A1 EP 2693124A1 EP 12179053 A EP12179053 A EP 12179053A EP 2693124 A1 EP2693124 A1 EP 2693124A1
Authority
EP
European Patent Office
Prior art keywords
pilot
burner
lance
face
liquid
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.)
Withdrawn
Application number
EP12179053.9A
Other languages
English (en)
French (fr)
Inventor
Michael Garlick
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 EP12179053.9A priority Critical patent/EP2693124A1/de
Publication of EP2693124A1 publication Critical patent/EP2693124A1/de
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—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
    • F23D—BURNERS
    • F23D2212/00—Burner material specifications
    • F23D2212/20—Burner material specifications metallic
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/00016—Preventing or reducing deposit build-up on burner parts, e.g. from carbon
    • 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
    • F23R2900/00004—Preventing formation of deposits on surfaces of gas turbine components, e.g. coke deposits

Definitions

  • the present invention is related to a pilot burner of a gas turbine engine, comprising a liquid pilot lance with a pilot lance face, wherein the pilot burner is made of a ferrous material. Further the invention is related to burner of a gas turbine engine, a combustor of a gas turbine engine and a gas turbine engine.
  • Air assist holes and outlet orifice are critical for atomisation and ignition of the liquid fuel and so blockages of the air outlet orifices can deteriorate the quality of the atomisation which can result in failed liquid fuel starts and inhibit liquid fuel operation.
  • pilot burner of a gas turbine engine according to independent claim 1 a burner of a gas turbine engine according to independent claim 12, a combustor of a gas turbine engine according to independent claim 13 and a gas turbine engine according to independent claim 14. Further features and details of the present invention result from the sub claims, the description and the drawings. Features and details discussed with respect to the pilot burner can also be applied to the burner, the combustor and the gas turbine engine and vice versa.
  • aforesaid objects are solved by a pilot burner of a gas turbine engine, comprising a liquid pilot lance with a pilot lance face, wherein the pilot burner is made of a ferrous material, characterized in that a face of the pilot burner and/or the pilot lance face comprise additionally a boron layer.
  • the pilot lance face of the liquid pilot lance is directed to the burning zone of a combustor of a gas turbine engine.
  • Such a pilot burner or such a liquid pilot lance of a pilot burner can be operated over a long time and has an improved liquid fuel starting reliability.
  • the pilot burner face, the pilot lance face and therefore the liquid pilot lance have an improved and extended life cycle compared to the known pilot burner, pilot lances faces and liquid pilot lances, because of the boron layer at the pilot burner face and/or the pilot lance face.
  • the boron layer has been boronised to the pilot burner face and/or the pilot lance face in a thermo-chemical hardening process. That means a boron layer is in the sense of the invention a boronised layer at the pilot burner face and/or the pilot lance face of a liquid pilot lance of the pilot burner.
  • Boronising is a thermo-chemical surface hardening process in which boron atoms are diffused into the surface of a ferrous material to form complex borides with the base metal. That means, there is no mechanical interface between the complex borides and the substrate as boronising is a true diffusion process.
  • the boron layer is hard and can comprise a slippery surface.
  • the boron layer is capable of sustain use at high temperatures. In other words, such a pilot burner face and/or such a pilot lance face and therefore such a liquid pilot lance have a high stability at high temperatures.
  • the boron layer is resistant to temperatures till or over 600-650°C.
  • the ferrous material of the pilot burner can be for example carbon steel, low alloy steel, stainless steel, tool steel, etc.
  • the liquid pilot lance is metallic. Preferred the liquid pilot lance is made of IN625 with less than 5% Fe.
  • HV Vickers Hardness
  • An advantage of such boron layer is that the boron layer has an improved adhesion compared to conventional hard material coatings.
  • Another advantage of such boron coated pilot burner face and/or the pilot lance face is that the pilot burner face and/or the pilot lance face have a high resistance against adhesive and abrasive wear.
  • pilot burner face and/or such a liquid pilot lance of a pilot burner can prevent that carbon build-up on the pilot lance face takes place.
  • the pilot burner face and/or the pilot lance face have a reduced coefficient of friction.
  • the boron layer at the pilot burner face and/or the pilot lance face is a mechanically stable layer which reduces the rate and severity of carbon deposition thus minimising any carbon build-up on the pilot burner face and/or the pilot lance face.
  • the boron layer reduces the carbon build-up at the outlet orifice for the liquid fuel and at the at least one outlet orifice for the air at the pilot burner face and/or the pilot lance face.
  • the boron layer at the pilot burner face and/or the pilot lance face can extend the life of the pilot burner face and/or the pilot lance face and thus the life of the liquid pilot lance of the pilot burner and the life of the pilot burner. Another advantage is the benefit with respect to the service of the pilot burner and/or the liquid pilot lance of the pilot burner.
  • the boron layer at the pilot burner face and/or the pilot lance face enables an improved atomisation of liquid fuel resulting in an improved ignition of the liquid pilot lance.
  • an advantageous liquid pilot lance is characterised in that the outlet orifice for the liquid fuel is arranged coaxial to a longitudinal axis of the liquid pilot lance and two or more outlet orifices for the air are surrounding the outlet orifice for the liquid fuel.
  • the outlet orifice for the liquid fuel can be arranges offset to the outlet orifices for the air.
  • the outlet orifice for the liquid fuel and the outlet orifices for the air are arranged next to each other in a plane.
  • a liquid pilot lance is preferred, which is characterized in that the two or more outlet orifices for the air are arranged at a circular path with the outlet orifice for the liquid fuel in the centre of the circular path.
  • Such a liquid pilot lance guarantees a good mixing of liquid fuel and air. Because of the boronised layer at the pilot lance face the deposition of carbon can be reduced at the pilot lance face.
  • the outlet orifice for the liquid fuel and/or the at least one outlet orifice for the air of a liquid pilot lance comprise/comprises a boron layer.
  • a liquid pilot lance is preferred which is characterised in that the fuel outlet and/or the air outlets comprise a boronised layer.
  • Such a liquid pilot lance minimises any carbon build-up on the air assist holes.
  • the atomisation of liquid fuel can be improved.
  • the ignition of the liquid pilot lance can be improved, as well.
  • the boron layer prevents carbon building at the outlet orifices. Thus a good and steady exhaust of liquid fuel and air can be reached.
  • a further preferred liquid pilot lance is characterized in that the liquid fuel duct and/or the at least one air duct comprise/comprises a boron layer. This reduces the carbon build-up at the end of the liquid fuel duct and/or at the at least one air duct. Such a liquid pilot lance reduces the possibility of a blockage at the end of the liquid fuel duct and the end of the at least one air duct because of the minimised carbon building at these areas.
  • the boron layer at the pilot burner face and/or the pilot lance face of the liquid pilot lance provides good resistance against abrasive and adhesive wear, high temperatures, corrosion and carbon build-up.
  • the boron layer increases the lifetime of the pilot burner face and/or the liquid pilot lance and thus of a pilot burner and a combustor comprising such a pilot burner and/or such a liquid pilot lance.
  • All kind of steel can be processed, but alloy elements reduce adhesion. Therefore, a liquid pilot lance is preferred, wherein the pilot lance face comprises a Nickel-Titanium-alloy or a Nickel-Titanium-based-alloy, in particular IN625.
  • the boron layer thickness can be between 50-350 ⁇ m, in particular between 250-350 ⁇ m for abrasive resistance.
  • the pilot burner face and/or the pilot lance face can be uneven.
  • the liquid lance face can be shaped wavelike.
  • pilot burner with a pilot burner face and/or a pilot lance face which are planar.
  • a planar pilot burner face and/or a planar pilot lance face with a boron layer minimise the deposition of carbon at the pilot lance face.
  • pilot lance face and the pilot lance body of a liquid pilot lance are formed in one piece, in particular monolithic.
  • a liquid pilot lance is preferred which is characterized in that the pilot lance face is an extra plate which is fixed at the front of the pilot lance body.
  • Such a pilot lance face is replaceable. In case of an extensive carbon build-up at the pilot lance face, only the pilot lance face has to be removed and not the pilot lance body, as well.
  • a burner of a gas turbine engine comprising at least a pilot burner according to the first aspect of the invention, in particular according to one of the claims 1 to 11.
  • the pilot burner comprises air ducts with merge into the air ducts of the liquid pilot lance.
  • a combustor of a gas turbine engine comprising a burner according to the second aspect of the invention.
  • the combustor can have two or more burner.
  • the combustor provides the same advantages, which have been discussed in detail as to the pilot burner according to the first aspect of the invention.
  • gas turbine engine comprising at least one pilot burner according to the first aspect of the invention, in particular according to one of the claims 1 to 11.
  • the gas turbine engine can comprise one or more burner and one or more combustors with one or more pilot burner each burner and combustor, respectively.
  • the gas turbine engine provides the same advantages, which have been discussed in detail as to the pilot burner according to the first aspect of the invention.
  • a burner 1 with a pilot burner 12 comprising a liquid pilot lance 4 with carbon deposit 11 at the pilot lance face 6 is disclosed.
  • Such carbon build-up 11 occurs at pilot lance faces 6, if liquid fuel is running out of the liquid fuel outlet orifice 7, shown in Fig. 2 .
  • the carbon build-up 11 on the pilot lance face 6 can lead to blockage of the air orifice outlets 8, see Fig. 2 .
  • the air outlet orifices 8 are essential for the atomisation and ignition of the liquid fuel and so blockages of the air outlet orifices 8 can deteriorate the quality of the atomisation which can result in failed liquid fuel starts and inhibit liquid fuel operation.
  • Such a carbon build-up 11 can occur at the face 14 of the pilot burner 12, as well, with the same disadvantages like at the pilot lance faces 6.
  • the burner 1 comprises a pilot burner 12 with one or more air ducts. Further, the burner 1 comprises a liquid pilot lance 4 with a liquid fuel duct 2 and two or more air ducts 3.
  • the liquid pilot lance 4 comprises a pilot lance body 5 and a pilot lance face 6.
  • the ducts 2, 3 lead to the pilot lance face 6.
  • the pilot lance face 6 comprises a liquid fuel outlet orifice 7 and air outlet orifices 8.
  • the pilot lance body 5 and the pilot lance face 6 are made of ferrous material.
  • Fig. 2 shows schematically a liquid pilot lance 4 with a pilot lance face 6 comprising a boron layer 10 at the pilot lance face 6. That means, in a thermo-chemical surface treatment of boronising of the pilot lance face 6 a mechanically stable boron 10 layer has been deposited at the pilot lance face 6.
  • the boron layer 10 reduces the rate and severity of carbon deposition thus minimising any carbon build-up 11 on the air outlet orifices 8 and the liquid fuel outlet orifice 7, extending the life of the liquid pilot lance 4.
  • the boron layer 10 is very hard.
  • the boron layer 10 is capable of sustain use at high temperatures.
  • the pilot lance face 6 with such a boron layer 10 and thus a liquid pilot lance 4 with such a pilot lance face 6 have a high stability at high temperatures.
  • the boron layer is resistant to temperatures over 550-650°C or more.
  • the boron layer 10 at the pilot lance face 6 is a mechanically stable layer which reduces the rate and severity of carbon deposition thus minimising any carbon build-up on pilot lance face 6. Further, the boron layer 10 reduces the carbon build-up at the liquid fuel outlet orifice 7 and at the air outlet orifices 8 at the pilot lance face 6.
  • the boron layer 10 is polished. Such a polished boron layer 10 reduces the carbon build-up 11 once more.
  • the polished boron layer 10 increases the atomisation of liquid fuel resulting in an improved ignition of the liquid pilot lance 4.
  • Such a liquid pilot lance 4 improves the liquid fuel starting reliability and extends the lifetime of the liquid pilot lance 4.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Spray-Type Burners (AREA)
EP12179053.9A 2012-08-02 2012-08-02 Pilotbrenner, Brenner, Brennkammer und Gasturbinenmotor Withdrawn EP2693124A1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP12179053.9A EP2693124A1 (de) 2012-08-02 2012-08-02 Pilotbrenner, Brenner, Brennkammer und Gasturbinenmotor

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP12179053.9A EP2693124A1 (de) 2012-08-02 2012-08-02 Pilotbrenner, Brenner, Brennkammer und Gasturbinenmotor

Publications (1)

Publication Number Publication Date
EP2693124A1 true EP2693124A1 (de) 2014-02-05

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP12179053.9A Withdrawn EP2693124A1 (de) 2012-08-02 2012-08-02 Pilotbrenner, Brenner, Brennkammer und Gasturbinenmotor

Country Status (1)

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EP (1) EP2693124A1 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3078913A1 (de) * 2015-04-09 2016-10-12 Siemens Aktiengesellschaft Brennkammerbrenneranordnung

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5315822A (en) * 1991-12-20 1994-05-31 United Technologies Corporation Gas turbine elements rearing coke inhibiting coatings of titanium compounds
EP0849533A2 (de) * 1996-12-19 1998-06-24 Asea Brown Boveri AG Brenneranordnung für eine Gastrubine
WO1999060075A1 (en) * 1998-05-15 1999-11-25 Conoco Inc. Improved delayed coker unit furnace
US20060027232A1 (en) * 2004-08-04 2006-02-09 Siemens Westinghouse Power Corporation Pilot nozzle heat shield having connected tangs
EP1914329A1 (de) * 2006-10-16 2008-04-23 Siemens Aktiengesellschaft Vorrichtung und Verfahren zur Erhöhung der Betriebsdauer von Feuerungsanlagen

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5315822A (en) * 1991-12-20 1994-05-31 United Technologies Corporation Gas turbine elements rearing coke inhibiting coatings of titanium compounds
EP0849533A2 (de) * 1996-12-19 1998-06-24 Asea Brown Boveri AG Brenneranordnung für eine Gastrubine
WO1999060075A1 (en) * 1998-05-15 1999-11-25 Conoco Inc. Improved delayed coker unit furnace
US20060027232A1 (en) * 2004-08-04 2006-02-09 Siemens Westinghouse Power Corporation Pilot nozzle heat shield having connected tangs
EP1914329A1 (de) * 2006-10-16 2008-04-23 Siemens Aktiengesellschaft Vorrichtung und Verfahren zur Erhöhung der Betriebsdauer von Feuerungsanlagen

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3078913A1 (de) * 2015-04-09 2016-10-12 Siemens Aktiengesellschaft Brennkammerbrenneranordnung

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