EP3354984A1 - Gelappter injektor für eine gasturbinenbrennkammer - Google Patents
Gelappter injektor für eine gasturbinenbrennkammer Download PDFInfo
- Publication number
- EP3354984A1 EP3354984A1 EP17154085.9A EP17154085A EP3354984A1 EP 3354984 A1 EP3354984 A1 EP 3354984A1 EP 17154085 A EP17154085 A EP 17154085A EP 3354984 A1 EP3354984 A1 EP 3354984A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- lobed
- injection
- vortex generators
- trailing edge
- finger according
- 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.)
- Granted
Links
- 238000000926 separation method Methods 0.000 claims abstract description 22
- 239000000446 fuel Substances 0.000 claims abstract description 20
- 238000002347 injection Methods 0.000 claims abstract description 12
- 239000007924 injection Substances 0.000 claims abstract description 12
- 238000001816 cooling Methods 0.000 claims description 3
- 230000035515 penetration Effects 0.000 claims description 3
- 239000007789 gas Substances 0.000 description 17
- 238000002485 combustion reaction Methods 0.000 description 6
- 239000000203 mixture Substances 0.000 description 6
- 206010016754 Flashback Diseases 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000004907 flux Effects 0.000 description 2
- 230000003993 interaction Effects 0.000 description 2
- 239000007788 liquid Substances 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- 239000007800 oxidant agent Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 239000003345 natural gas Substances 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
- 230000002269 spontaneous effect Effects 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
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
- F23R3/34—Feeding into different combustion zones
- F23R3/346—Feeding into different combustion zones for staged 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
- 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
- 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
- F23R2900/03341—Sequential combustion chambers or burners
Definitions
- the present invention relates to the technology of gas turbines. It refers to a lobed injector for a gas turbine combustor according to the preamble of claim 1
- FIG. 1 An exemplary gas turbine of the applicant with sequential combustion is shown in Fig. 1 .
- Gas turbine 10 of Fig. 1 comprises a rotor 11 with a plurality of blades rotating about a machine axis 20 and being surrounded by a casing 12. Air is taken in at air inlet 13 and is compressed by compressor 14. The compressed air is used to burn a first fuel in a first (annular) combustor 15, thereby generating hot gas. The hot gas drives a first, high pressure (HP) turbine 16, is then reheated in a second (annular, sequential) combustor 17, drives a second, low pressure (LP) turbine 18 and exits gas turbine 10 through exhaust gas outlet 19.
- HP high pressure
- LP low pressure
- the operating conditions allow self ignition (spontaneous ignition) of the fuel air mixture without additional energy being supplied to the mixture.
- the residence time therein must not exceed the auto ignition delay time.
- This criterion ensures flame-free zones inside the burner.
- This criterion poses challenges in obtaining appropriate distribution of the fuel across the burner exit area. SEV-burners are currently designed for operation on natural gas and oil only. Therefore, the momentum flux of the fuel is adjusted relative to the momentum flux of the main flow so as to penetrate into the vortices.
- the subsequent mixing of the fuel and the oxidizer at the exit of the mixing zone is just sufficient to allow low NOx emissions (mixing quality) and avoid flashback (residence time), which may be caused by auto ignition of the fuel air mixture in the mixing zone.
- lobed fingers having nozzles to inject oil/fuel and carrier air in the burner and/or mixer.
- One phenomenon that may occur at the outlet of nozzles of lobed fingers is the separation of the mixture of gases and oil/fuel from the fingers. Disadvantages related to flow separation are: a weak pressure gradient; a mixing vortex generates at a larger distance from the nozzle than where there is no separation; separation generates a bubble creating a pressure loss along the flow; and a separation region is a potential flame holder in the reheat combustion and this increases flashback risk.
- the invention is accordingly based on the object of providing a lobed injector able to avoid the above-mentioned separation and, at the same time, provide enhanced mixing.
- a lobed injector finger for a burner or a mixer of a gas turbine comprising a leading edge, a lobed trailing edge, a fist and a second corrugated surfaces defining an airfoil cross section and converging in the trailing edge, a plurality of nozzles located at the trailing edge for injection of oil or fuel or carrier air in the burner or mixer, and a plurality of vortex generators projecting from a suction side of lobes defined by the first and second corrugated surfaces and positioned from the nozzles to reduce flow separation and/or influence the location of a separation bubble.
- grouped or alternating neighbouring lobed fingers are the cause to have local combined vortices (grouped) or not (alternating); thus it defines the level of large scale mixing of fuel, cooling air and hot gas.
- the arrangement is defined based on the burner size and possible number of lobed fingers. With current rectangular sequential burner, a four finger arrangement is proper. However, the arrangements will not be limited to four finger arrangement.
- an arrangement of three lobed fingers behaves differently than an arrangement with four fingers or more.
- grouped lobes allow the vortices to combine with each other (two or more vortices can combine into a single vortex) and thereby create large scale structures, which enhance mixing and are thus beneficial for NOx, CO and overall temperature distribution factor (OTDF).
- the lobed fingers according to the present invention can also be used in mixers and/or burners of a gas turbine.
- the burner may be either annular or rectangular and the relative combustor may be either an annular combustor or a can combustor.
- Lobe lance 21 of Fig. 2 which is preferably to be used with a rectangular burner, comprises four separate fingers 22a-d extending in parallel between an upper plate 25 and a lower plate 26.
- Each finger 22 is configured as a streamlined body which has a streamlined cross-sectional profile (like an airfoil).
- the body has two lateral surfaces essentially parallel to an axial hot gas flow with inflow direction 32, which passes through the lance between upper and lower plates 25, 26.
- the lateral surfaces are joined at their upstream side by a leading edge 23 and joined at their downstream side forming a trailing edge 24.
- a plurality of nozzles 27 for injecting a gaseous and/or liquid fuel mixed with air is distributed along the trailing edge 24.
- Each of said fingers 22 has an air plenum 30 for air supply, a gas plenum 31 for gaseous fuel supply, and a liquid fuel supply 29.
- Means for improving the mixing quality and reducing pressure loss in said secondary combustor are provided in the trailing edge region of said body in form of lobes 28 running between the nozzles 27 at the trailing edge 24.
- Lobes 28 of the various fingers 22 generate vortices in the downstream flow of the fuel/air mixture, whereby the vortex flow of the different fingers 22 interact with each other. This interaction, which is able to enhance the mixing effect, depends on the orientation of lobes 28 in each finger.
- the lobes 28 of the different fingers 22a-d may have two different orientations.
- the lobes 28 of the left two fingers 22a and 22b have the same orientation, which is opposite to the orientation of the lobes 28 of the right two fingers 22c and 22d.
- the lobe orientation of fingers 22a and 22b is said to be R (for right), while the lobe orientation of fingers 22c and 22d is said to be L (for left).
- Fig. 2 shows, in a bottom right corner, rotation direction of vortexes due to lobes at the outlet of two nozzle 27.
- Each vortex is induced by the pressure difference between two corrugated surfaces 40a and 40b of fingers 22, which surfaces converge and are joined along corrugated trailing edge 24 where nozzles 27 are located.
- surfaces 40 define the airfoil cross section of finger 22.
- fingers 22 comprises a plurality of vortex generators, in particular micro vortex generators, projecting from corrugated surfaces 40a, 40b to control in a passive way the flow in the region of lobes 28.
- Fig. 3-4 depict respective enlarged suction or concave sides of a lobe 28.
- vortex generators 42 are set in an array and are substantially parallel to one another and substantially parallel to a transversal direction D perpendicular to a straight line connecting the axes of two adjacent nozzles 27. By guiding the flow along direction L, separation is substantially prevented.
- direction D is parallel to direction 32.
- location along the flow direction is such that vortex generators 42 intercept a plane containing the axes of two adjacent nozzles 27. A trace of such a plane is the straight vertical line of figure 3 connecting the axes of nozzles 27.
- vortex generators 42 are located between such plane and trailing edge 24, as shown in Fig. 3 . Such a location provides an improved interaction with the flow in order to decrease separation.
- vortex generators 42 are inclined with respect to direction D such that a trailing edge 43 of a vortex generator 42 is proximal to a respective nozzle 27 and a leading edge 44 of the vortex generator 42 is distal from the respective nozzle 27.
- Vortex generators 42 of fig. 4 are divergent along inflow direction 32. According to the layout of fig. 4 , the separation is not prevented but the bubble is forced to be in a position with a low or null influence to the reheat combustion.
- vortex generators 42 of fig. 4 control the flow in the surroundings of the relative nozzle 27 in a region A1 at the convergence of lobe 28 with the relative nozzle 27. In such regions, boundary layer flow is accelerated to prevent separation.
- vortex generators 42 of figure 4 locate separation, if any, in a transversal tip region A2 of lobe 28 that is far away, in particular furthest away, from nozzles 27. In this way there is little if any impact of possible separation in the area of nozzles 27.
- location of vortex generators of Fig. 4 is the same as that described in the previous paragraph.
- Fig. 4 shows an example of vortex generators 42 intercepting the plane containing the axes of two adjacent nozzles.
- vortex generators 42 may have additional positions on the suction side of the respective lobe 28.
- Fig. 5a shows a preferred two dimensional embodiment of a vortex generator 42 having a fin-like or substantially triangular shape with a length L along surfaces 40a or 40b, a height H that is proximal to or coincides with trailing edge 43 and a width W, preferably a constant width.
- Figure 5b shows an alternative and three-dimensional embodiment of a vortex generator 42, having a tetrahedral shape.
- Figure 5c shows a further three-dimensional embodiment obtained by halving the tetrahedral shape of Fig. 5b with a symmetry plane.
- a trailing half portion TP of vortex generator 42 has a maximum height that is greater than a maximum height of a leading half portion LP.
- a leading portion and a trailing portion of vortex generator 42 are defined with respect to flow direction (shown by the arrow of Fig. 5b ).
- embodiments of Fig. 5 show a maximum height of the vortex generator 42 defined by the relative trailing edge 43.
- preferred dimensional ranges for the shape of vortex generators 42 are: 5-10 mm length and less than 4 mm height.
- maximum width is 1-2 mm. Incidence with inflow is equal or less than 5°: figure 4 is therefore not in scale.
- incidence is measured with reference to a mid-plane.
- Vortex generators 42 are applicable to any lobed finger 22.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Nozzles For Spraying Of Liquid Fuel (AREA)
- Spray-Type Burners (AREA)
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP17154085.9A EP3354984B1 (de) | 2017-01-31 | 2017-01-31 | Gelappter injektor für eine gasturbinenbrennkammer |
CN201810094747.6A CN108375082B (zh) | 2017-01-31 | 2018-01-31 | 用于燃气涡轮机燃烧器的波瓣状喷射器 |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP17154085.9A EP3354984B1 (de) | 2017-01-31 | 2017-01-31 | Gelappter injektor für eine gasturbinenbrennkammer |
Publications (2)
Publication Number | Publication Date |
---|---|
EP3354984A1 true EP3354984A1 (de) | 2018-08-01 |
EP3354984B1 EP3354984B1 (de) | 2020-09-09 |
Family
ID=57960291
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP17154085.9A Active EP3354984B1 (de) | 2017-01-31 | 2017-01-31 | Gelappter injektor für eine gasturbinenbrennkammer |
Country Status (2)
Country | Link |
---|---|
EP (1) | EP3354984B1 (de) |
CN (1) | CN108375082B (de) |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
RU2769773C2 (ru) * | 2018-12-25 | 2022-04-05 | Ансальдо Энергия Свитзерленд Аг | Модульная инжекционная головка для камеры сгорания газовой турбины |
Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4932861A (en) | 1987-12-21 | 1990-06-12 | Bbc Brown Boveri Ag | Process for premixing-type combustion of liquid fuel |
US5431018A (en) | 1992-07-03 | 1995-07-11 | Abb Research Ltd. | Secondary burner having a through-flow helmholtz resonator |
US5626017A (en) | 1994-07-25 | 1997-05-06 | Abb Research Ltd. | Combustion chamber for gas turbine engine |
US20020187448A1 (en) | 2001-06-09 | 2002-12-12 | Adnan Eroglu | Burner system |
US20140123665A1 (en) * | 2012-10-25 | 2014-05-08 | Alstom Technology Ltd | Reheat burner arrangement |
US20160146468A1 (en) * | 2014-11-20 | 2016-05-26 | General Electric Technology Gmbh | Fuel lance cooling for a gas turbine with sequential combustion |
US20160146470A1 (en) * | 2014-11-26 | 2016-05-26 | General Electric Technology Gmbh | Burner of a gas turbine |
Family Cites Families (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE59401018D1 (de) * | 1993-04-08 | 1996-12-19 | Abb Management Ag | Mischkammer |
DE19527453B4 (de) * | 1995-07-27 | 2009-05-07 | Alstom | Vormischbrenner |
US20090173074A1 (en) * | 2008-01-03 | 2009-07-09 | General Electric Company | Integrated fuel nozzle ifc |
EP2496880B1 (de) * | 2009-11-07 | 2018-12-05 | Ansaldo Energia Switzerland AG | Injektionssystem für einen nachbrenner |
EP2703721B1 (de) * | 2012-08-31 | 2019-05-22 | Ansaldo Energia IP UK Limited | Vormischbrenner |
CA2830031C (en) * | 2012-10-23 | 2016-03-15 | Alstom Technology Ltd. | Burner for a can combustor |
EP3056819B1 (de) * | 2015-02-11 | 2020-04-01 | Ansaldo Energia Switzerland AG | Kraftstoffeinspritzungsvorrichtung für eine Gasturbine |
US10458655B2 (en) * | 2015-06-30 | 2019-10-29 | General Electric Company | Fuel nozzle assembly |
-
2017
- 2017-01-31 EP EP17154085.9A patent/EP3354984B1/de active Active
-
2018
- 2018-01-31 CN CN201810094747.6A patent/CN108375082B/zh active Active
Patent Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4932861A (en) | 1987-12-21 | 1990-06-12 | Bbc Brown Boveri Ag | Process for premixing-type combustion of liquid fuel |
US5431018A (en) | 1992-07-03 | 1995-07-11 | Abb Research Ltd. | Secondary burner having a through-flow helmholtz resonator |
US5626017A (en) | 1994-07-25 | 1997-05-06 | Abb Research Ltd. | Combustion chamber for gas turbine engine |
US20020187448A1 (en) | 2001-06-09 | 2002-12-12 | Adnan Eroglu | Burner system |
US20140123665A1 (en) * | 2012-10-25 | 2014-05-08 | Alstom Technology Ltd | Reheat burner arrangement |
US20160146468A1 (en) * | 2014-11-20 | 2016-05-26 | General Electric Technology Gmbh | Fuel lance cooling for a gas turbine with sequential combustion |
US20160146470A1 (en) * | 2014-11-26 | 2016-05-26 | General Electric Technology Gmbh | Burner of a gas turbine |
Also Published As
Publication number | Publication date |
---|---|
CN108375082A (zh) | 2018-08-07 |
EP3354984B1 (de) | 2020-09-09 |
CN108375082B (zh) | 2021-05-25 |
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