EP3088802A1 - Buse pour un lobe de combustion de turbine a gaz - Google Patents

Buse pour un lobe de combustion de turbine a gaz Download PDF

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Publication number
EP3088802A1
EP3088802A1 EP16165158.3A EP16165158A EP3088802A1 EP 3088802 A1 EP3088802 A1 EP 3088802A1 EP 16165158 A EP16165158 A EP 16165158A EP 3088802 A1 EP3088802 A1 EP 3088802A1
Authority
EP
European Patent Office
Prior art keywords
nozzle
channel
outlet
fuel
swirl
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Withdrawn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
EP16165158.3A
Other languages
German (de)
English (en)
Inventor
Douglas Pennell
Thorsten Motzkus
Martin Zajadatz
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.)
General Electric Technology GmbH
Original Assignee
General Electric Technology GmbH
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 General Electric Technology GmbH filed Critical General Electric Technology GmbH
Priority to EP16165158.3A priority Critical patent/EP3088802A1/fr
Publication of EP3088802A1 publication Critical patent/EP3088802A1/fr
Withdrawn legal-status Critical Current

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Classifications

    • 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
    • F23D11/38—Nozzles; Cleaning devices therefor
    • F23D11/383—Nozzles; Cleaning devices therefor with swirl 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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means

Definitions

  • the present disclosure relates to a nozzle for a gas turbine combustor, and particularly to a nozzle for a gas turbine combustor with a swirl channel and an inner channel.
  • Today's nozzle systems for gas turbine combustors are mostly designed as plain jet or swirl nozzles.
  • the main differences between these nozzle types are atomising quality, spray cone angle and pressure drop.
  • Swirl nozzles provide good atomising combined with large spray cone angles.
  • plain jets provide a lower fuel pressure drop, but also worse atomising quality and smaller spray cone angles.
  • a plain jet nozzle consists of an axial bore hole, and the corresponding manufacturing costs are low.
  • the plain jet nozzle also requires less space in the combustor compared to a swirl nozzle.
  • Swirl nozzles generally have a geometrically complex swirler combined with a sophisticated nozzle exit shape, and therefore provide better spray quality.
  • the manufacturing costs for swirl nozzles can be a great deal larger than for plain jet nozzles, although as a result of the better spray quality a greater operation range can be available.
  • a first aspect of the invention provides a nozzle for a gas turbine combustor, the nozzle comprising an inner channel, a swirl channel, a mixing zone and an outlet channel, wherein the nozzle extends from an inlet to an outlet, the swirl channel is disposed around the inner channel, the inner channel and the swirl channel extend from the inlet to the mixing zone, the mixing zone extends from the inner channel and the swirl channel to the outlet channel, and the outlet channel extends from the mixing zone to the outlet.
  • the nozzle can also provide some of the advantages of a plain jet nozzle and a swirl nozzle within the same nozzle, and can provide an optimised compromise between the two designs.
  • the nozzle can also be made smaller than a swirl nozzle.
  • the nozzle is arranged such that when in use 30 to 75% of a fuel goes through the inner channel.
  • the nozzle comprises a diffuser attached to the outlet channel and wherein the outlet channel extends from the mixing zone to the diffuser. The diffuser can enhance the spray angle and improve mixing with air to reduce hot spots in the combustion chamber and thereby increase lifetime and reduce emissions.
  • the diameter of the inner channel is smaller than the diameter of the outlet channel.
  • the flow number of the nozzle can be corrected even when the nozzle is in place in a gas turbine by reaming the inner channel.
  • the nozzle is for use with a liquid fuel such as fuel oil, kerosene, diesel oil, or an emulsion of fuel oil, kerosene or diesel oil with water.
  • a liquid fuel such as fuel oil, kerosene, diesel oil, or an emulsion of fuel oil, kerosene or diesel oil with water.
  • Use of an emulsion fuel can reduce the peak burning temperature and reduce emissions, particularly of NOx.
  • the outlet channel opens directly into a combustion chamber.
  • a second aspect of the invention provides a burner comprising the nozzle as described above.
  • the burner comprises at least one shielding fluid hole disposed around the outlet of the nozzle.
  • a shielding fluid such as air provided through the shielding fluid holes can help protect the nozzle and other nearby parts from heat (when the nozzle is not being used), and from the fuel and from coke formation when in use.
  • a third aspect of the invention provides a gas turbine comprising a combustor comprising the nozzle as described above or the burner as described above.
  • a fourth aspect of the invention provides a method of using a nozzle for a gas turbine combustor, the nozzle comprising an inner channel, a swirl channel, a mixing zone and an outlet channel and the nozzle having an inlet and an outlet, wherein the swirl channel is disposed around the inner channel, the inner channel and the swirl channel extend from the inlet to the mixing zone, the mixing zone extends from the inner channel and the swirl channel to the outlet channel, and the outlet channel extends from the mixing zone to the outlet, the method comprising feeding a fuel through the nozzle and combusting the fuel in a combustion chamber.
  • the fuel is a liquid fuel such as fuel oil, kerosene, diesel oil, or an emulsion of fuel oil, kerosene or diesel oil with water.
  • Figure 1 shows a nozzle 1 according to the invention in a burner 8 for a gas turbine.
  • the nozzle comprises at least one inner channel 3 (inner axial inlet channel) with at least one swirl channel 4 (outer swirl channel) extending around the outer diameter of the inner channel 3.
  • the inner channel 3 and the swirl channel 4 extend from a nozzle inlet 20 to a mixing zone 5 downstream of the inner channel 3 and swirl channel 4.
  • the mixing zone 5 is a cylindrical hole through the nozzle, with the axis of the mixing zone cylindrical hole 16 being perpendicular to the axis 18 of the nozzle (see also Figure 2 ).
  • An outlet channel 6 is disposed at the other side of the mixing zone from the inner channel 3 and the swirl channel 4 (downstream of the mixing zone 5), with the outlet channel 6 extending from the mixing zone 5 to the outlet 22 of the nozzle.
  • a shielding fluid hole 10 (shielding fluid channel) is provided between a nozzle carrier 2 and the burner 8, for providing a shielding fluid such as cooling air.
  • the nozzle carrier 2 is part of a fuel supply line 9.
  • Figure 2 shows a side view of the nozzle of Figure 1 , with features as described above.
  • Figure 2 includes dashed lines showing the internal extent of the walls of the nozzle.
  • Figure 3 shows a cross-section view of the nozzle in the same direction as Figure 1 but without the surrounding burner.
  • Figure 3 is also a cross-section of the nozzle in Figure 2 along A-A.
  • An optional diffuser 24 is shown in Figure 3 , downstream of and attached at the outlet of the nozzle.
  • the nozzle and burner described above are for use in a gas turbine.
  • the nozzle could be used in an AEV burner (advanced environmental burner).
  • the nozzle can be used in a liquid fuel burner or as the liquid fuel nozzles in a combined gas and liquid fuel burner with both liquid fuel nozzles and gas nozzles.
  • fuel 14 When in use, fuel 14 is fed through the fuel supply line 9 and the nozzle carrier 2 to the inlet 20, where it splits into two flows, a main flow going through the inner channel 3 and a second flow going through the swirl channel 4. After flowing through the inner channel 3 and swirl channel 4 respectively, the main flow and the second flow recombine in the mixing zone 5. From the mixing zone 5, the fuel 14 flows through the outlet channel 6 and into the combustion chamber 7. If a diffuser is provided after the outlet, the fuel flows through the diffuser after leaving the outlet channel before entering the combustor.
  • the fuel can be a liquid fuel such as fuel oil, kerosene, diesel oil, or an emulsion of fuel oil, kerosene or diesel oil with water.
  • the fuel oil may be fuel oil number 2, for example (i.e. oil which is primarily made up of hydrocarbon molecules with chain lengths of between 10 and 20 carbon atoms).
  • a majority of the fuel goes through the inner channel, preferably at least 75%, more preferably at least 85% and most preferably at least 95%.
  • the remaining fuel goes through the swirl channel, generally at least 1% or 2%.
  • the maximum fuel flow fraction through the inner channel is therefore generally 98% or 99%.
  • 30 to 75% of the fuel goes through the inner channel, preferably 40 to 70% and most preferably 55 to 60%.
  • One embodiment has 58% of the fuel going through the inner channel and 42% of the fuel going through the swirl channel, for example. This means that a part of the fuel goes directly through (is fed through) the inner channel, the mixing zone and the outlet channel into the combustor.
  • the remaining fuel takes the same path except that it goes through the swirl channel instead of through the inner channel, generating additional swirl and turbulence in the mixing zone. This can result in a fuel spray from the nozzle outlet with an improved spray quality compared to a plain jet nozzle.
  • Both the swirl of the fuel exiting the nozzle outlet and the number and position of fuel-rich zones in the fuel flow field in the combustor vary based on the mass flow ratio (between the inner channel and the swirl channel) and on the number of swirl channels.
  • the location of the fuel-rich zones in the fuel flow field is important, and fuel-rich zones should be kept away from other components in the combustor to minimise the thermal load on these components.
  • the orientation of the nozzle can be chosen to optimise the position of the fuel-rich zones and minimise the thermal load.
  • the nozzle 1 may be manufactured as an integral part or as several separate parts. Generally, the nozzle 1 is then attached to the nozzle carrier 2, which is then attached to the fuel supply line 9. The nozzle 1 may be attached to the nozzle carrier 2 by any appropriate method, such as brazing or welding. The join between the nozzle 1 and the nozzle carrier 2 is generally gas-tight. Similarly, the nozzle carrier 2 may attached to the fuel supply line 9 by any appropriate method, such as brazing or welding.
  • the inner channel Before, during or after insertion of the nozzle into the gas turbine, the inner channel may be reamed to increase its inner diameter; that is, its diameter in a plane perpendicular to the nozzle axis 18. This can be useful if the nozzle is outside of a tolerance band after initial manufacture, or is found subsequently to be outside of a tolerance band.
  • the nozzle may be retrofitted to existing gas turbines.
  • the nozzle is generally a cylindrical or substantially cylindrical shape, although other shapes are also possible.
  • the cross-section of the nozzle in the plane perpendicular to the nozzle axis 18 is generally circular, although again other shapes are possible.
  • the nozzle can be part of a combustor, and can lead fuel directly to a combustion chamber after the outlet of the nozzle. If a diffuser is provided, the fuel exits through the outlet into the diffuser and then into the combustion chamber.
  • One, two or more inner channels 3 may be provided.
  • the inner channel may have a smaller diameter than the outlet channel, as can be seen in the Figures. However, the inner channel may alternatively have the same or a larger diameter than the outlet channel.
  • One, two or more swirl channels 4 may be provided.
  • the swirl channel(s) and the inner channel(s) are preferably concentric.
  • the swirl channel may be disposed around the entire circumference (relative to the nozzle axis direction) of the inner channel.
  • the mixing zone 5 is shown as a cylindrical hole through the nozzle, but may be other shapes and at other angles, such as a cuboid or ovoid shape or an irregular shape.
  • the nozzle carrier 2 is shown in Figure 1 extending around the nozzle and beyond the inlet 20 of the nozzle. Alternatively, the nozzle carrier may extend up to the inlet 20 of the nozzle, or may only extend part of the length of the nozzle (relative to the nozzle axis direction). Beyond the end of the nozzle carrier, the fuel supply line continues as shown in Figure 1 .
  • the nozzle carrier 2 (fuel supply line) may extend around the entire circumference (relative to the nozzle axis) of the nozzle. In the region of the nozzle carrier adjacent to the swirl channel 4, the nozzle carrier (or another portion of the fuel supply line) generally provides the outer limit of the swirl channel, as shown in Figure 1 . Alternatively, the structure of the nozzle itself may delimit the swirl channel.
  • the nozzle carrier 2 may also be an integral part of the fuel supply line 9.
  • the nozzle axis 18 may also be an axis of the fuel supply line.
  • the nozzle and the fuel supply line (nozzle carrier) may be concentric.
  • the shielding fluid hole 10 is optional, and the nozzle carrier 2 may be directly adjacent to the burner.
  • the burner can be attached to the nozzle carrier.
  • the shielding fluid hole may extend around the entire circumference of the nozzle (and nozzle carrier), or alternatively one or more shielding fluid holes may be provided that each only extend part of the way around the entire circumference. Supports may also be provided in the shielding fluid hole between the nozzle carrier and the burner, particularly in embodiments where the shielding fluid hole extends around the entire circumference.
  • the shielding fluid hole is normally further from the nozzle axis 18 than the inner channel 3 and the swirl channel 4.
  • the shielding fluid hole can provide an annulus of air through which the shielded fluid (i.e. the fluid from the inner channel and swirl channel) flows.
  • the diffuser may be a conical shape (conical frustum) or another appropriate shape, such as pyramidal.
  • the diffuser will generally conform to the shape of the outlet of the nozzle.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Spray-Type Burners (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)
  • Nozzles (AREA)
EP16165158.3A 2015-04-29 2016-04-13 Buse pour un lobe de combustion de turbine a gaz Withdrawn EP3088802A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP16165158.3A EP3088802A1 (fr) 2015-04-29 2016-04-13 Buse pour un lobe de combustion de turbine a gaz

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP15165682 2015-04-29
EP16165158.3A EP3088802A1 (fr) 2015-04-29 2016-04-13 Buse pour un lobe de combustion de turbine a gaz

Publications (1)

Publication Number Publication Date
EP3088802A1 true EP3088802A1 (fr) 2016-11-02

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP16165158.3A Withdrawn EP3088802A1 (fr) 2015-04-29 2016-04-13 Buse pour un lobe de combustion de turbine a gaz

Country Status (4)

Country Link
US (1) US20160320062A1 (fr)
EP (1) EP3088802A1 (fr)
CN (1) CN106091012A (fr)
RU (1) RU2016116770A (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108916911A (zh) * 2018-04-27 2018-11-30 北京航空航天大学 一种预燃级采用预膜板结构的中心分级低排放燃烧室头部

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108636625B (zh) 2018-03-13 2021-09-14 因诺弥斯特有限责任公司 多模式流体喷嘴

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3920187A (en) * 1974-05-24 1975-11-18 Porta Test Mfg Spray head
GB2001262A (en) * 1977-07-22 1979-01-31 Bayer Ag Atomizer nozzles
US5934555A (en) * 1996-03-05 1999-08-10 Abb Research Ltd. Pressure atomizer nozzle
US6045058A (en) * 1997-07-17 2000-04-04 Abb Research Ltd. Pressure atomizer nozzle
US20070231762A1 (en) * 2004-06-07 2007-10-04 Stefano Bernero Injector for Liquid Fuel, and Staged Premix Burner Having This Injector
US20100050647A1 (en) * 2008-09-01 2010-03-04 Rolls-Royce Plc Swirler for a fuel injector

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN86200959U (zh) * 1986-02-21 1986-12-03 中国人民解放军第五七○六工厂 双重雾化内燃式重油燃烧器
EP0902233B1 (fr) * 1997-09-15 2003-03-12 ALSTOM (Switzerland) Ltd Buse de pulvérisation par pression combinée
CA2584270C (fr) * 2004-10-18 2013-07-16 Alstom Technology Ltd. Bruleur pour turbine a gaz
CN201363721Y (zh) * 2009-02-13 2009-12-16 上海鸿臣实业有限公司 多重雾化混合燃烧器
US9127843B2 (en) * 2013-03-12 2015-09-08 Pratt & Whitney Canada Corp. Combustor for gas turbine engine

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3920187A (en) * 1974-05-24 1975-11-18 Porta Test Mfg Spray head
GB2001262A (en) * 1977-07-22 1979-01-31 Bayer Ag Atomizer nozzles
US5934555A (en) * 1996-03-05 1999-08-10 Abb Research Ltd. Pressure atomizer nozzle
US6045058A (en) * 1997-07-17 2000-04-04 Abb Research Ltd. Pressure atomizer nozzle
US20070231762A1 (en) * 2004-06-07 2007-10-04 Stefano Bernero Injector for Liquid Fuel, and Staged Premix Burner Having This Injector
US20100050647A1 (en) * 2008-09-01 2010-03-04 Rolls-Royce Plc Swirler for a fuel injector

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108916911A (zh) * 2018-04-27 2018-11-30 北京航空航天大学 一种预燃级采用预膜板结构的中心分级低排放燃烧室头部
CN108916911B (zh) * 2018-04-27 2019-12-03 北京航空航天大学 一种预燃级采用预膜板结构的中心分级低排放燃烧室头部

Also Published As

Publication number Publication date
US20160320062A1 (en) 2016-11-03
CN106091012A (zh) 2016-11-09
RU2016116770A (ru) 2017-11-02

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