EP3354984B1 - Gelappter injektor für eine gasturbinenbrennkammer - Google Patents

Gelappter injektor für eine gasturbinenbrennkammer Download PDF

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Publication number
EP3354984B1
EP3354984B1 EP17154085.9A EP17154085A EP3354984B1 EP 3354984 B1 EP3354984 B1 EP 3354984B1 EP 17154085 A EP17154085 A EP 17154085A EP 3354984 B1 EP3354984 B1 EP 3354984B1
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EP
European Patent Office
Prior art keywords
lobed
vortex generators
trailing edge
injection
gas turbine
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.)
Active
Application number
EP17154085.9A
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English (en)
French (fr)
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EP3354984A1 (de
Inventor
Yang Yang
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Ansaldo Energia Switzerland AG
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Ansaldo Energia Switzerland AG
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Priority to EP17154085.9A priority Critical patent/EP3354984B1/de
Priority to CN201810094747.6A priority patent/CN108375082B/zh
Publication of EP3354984A1 publication Critical patent/EP3354984A1/de
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    • 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.
  • US2016146470 discloses a burner of a gas turbine having a duct, a vortex generator extending in the duct and including a leading edge and a trailing edge, wherein the trailing edge has a first order lobed shape. US2016146470 provides a basis for the two-part form of claim 1.
  • US2014123665 discloses a reheat burner arrangement including a center body, an annular duct with a cross-section area and a plurality of lobed radially extending injection devices.
  • US2016146468 discloses a lobed injector finger for a burner a gas turbine.
  • 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.
  • 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.
  • 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.
  • Vortex generators 42 are applicable to any lobed finger 22.

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  • 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)

Claims (9)

  1. Gelappter Injektorfinger für einen Brenner oder einen Mischer einer Gasturbine, enthaltend eine Vorderkante (23), eine gelappte Hinterkante (24), eine erste und eine zweite gewellte Oberfläche (40a, 40b), die einen Tragflächenquerschnitt bilden und an der Hinterkante (24) konvergieren, und eine Vielzahl von Düsen (27), die an der Hinterkante (24) angeordnet sind, um Öl oder Brennstoff oder Trägerluft in den Brenner oder Mischer zu injizieren, wobei der gelappte Injektorfinger eine Vielzahl von Wirbelerzeugern (42) aufweist, die von einer Saugseite der Lappen (28) vorspringen, gebildet von der ersten und der zweiten gewellten Oberfläche (40a, 40b), und von den Düsen (27) positioniert, um die Strömungstrennung und/oder den Einfluss der Position einer Trennungsblase zu reduzieren; wobei die Wirbelerzeuger (42) in Bezug auf eine zu einer die Achsen von zwei benachbarten Düsen (27) verbindenden geraden Linie im wesentlichen senkrechten Richtung (D) geneigt sind; dadurch gekennzeichnet, dass die Wirbelerzeuger (42) zu der Hinterkante (24) hin divergieren, sodass ein Trennungsgebiet (A2) einer Querspitze des Lappens (28) benachbart lokalisiert ist und ein Grenzschichtstrom in einem an die Düse (27) angrenzenden Gebiet (A1) beschleunigt ist.
  2. Gelappter Injektorfinger nach Anspruch 1, dadurch gekennzeichnet, dass die Wirbelerzeuger (42) einen Einfallswinkel haben, der in Bezug auf eine Einströmungsrichtung (32) niedriger oder gleich 5° ist.
  3. Gelappter Injektorfinger nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass ein hinterer Halbteil (TP) des Wirbelerzeuger (42) eine erste maximale Höhe hat, die größer ist als eine zweite maximale Höhe eines vorderen Halbteils (LP) des Wirbelerzeugers (42).
  4. Gelappter Injektorfinger nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass die Wirbelerzeuger (42) eine dreieckige oder flossenförmige Form oder tetraederförmige Form oder halbtetraederförmige Form haben.
  5. Gelappter Injektorfinger nach Anspruch 4, dadurch gekennzeichnet, dass die Wirbelerzeuger (42) eine Höhe (H) von weniger oder gleich 4 mm und/oder eine Länge (L) zwischen 5 und 10 mm und/oder eine Breite (W) zwischen 1 und 2 mm haben.
  6. Gelappter Injektorfinger nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass ein Durchdringungswinkel der gelappten Hinterkante (24) größer als 40° ist.
  7. Gelappter Injektorfinger nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass auf Oberflächen (40a, 40b) im Bereich von annähernd 0,5 mm oder weniger keine Löcher vorgesehen sind, um einen Kühlfilm an der Saugseite vorzusehen.
  8. Brenner einer Gasturbine, enthaltend eine Vielzahl von gelappten Injektorfingern (22) nach einem der vorhergehenden Ansprüche.
  9. Mischer einer Gasturbine, enthaltend eine Vielzahl von gelappten Injektorfingern (22) nach einem der vorhergehenden Ansprüche.
EP17154085.9A 2017-01-31 2017-01-31 Gelappter injektor für eine gasturbinenbrennkammer Active EP3354984B1 (de)

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

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Application Number Priority Date Filing Date Title
EP17154085.9A EP3354984B1 (de) 2017-01-31 2017-01-31 Gelappter injektor für eine gasturbinenbrennkammer

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EP3354984A1 EP3354984A1 (de) 2018-08-01
EP3354984B1 true EP3354984B1 (de) 2020-09-09

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Families Citing this family (1)

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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

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Publication number Priority date Publication date Assignee Title
CH674561A5 (de) 1987-12-21 1990-06-15 Bbc Brown Boveri & Cie
DE59208193D1 (de) 1992-07-03 1997-04-17 Abb Research Ltd Nachbrenner
DE59401018D1 (de) * 1993-04-08 1996-12-19 Abb Management Ag Mischkammer
DE4426351B4 (de) 1994-07-25 2006-04-06 Alstom Brennkammer für eine Gasturbine
DE19527453B4 (de) * 1995-07-27 2009-05-07 Alstom Vormischbrenner
DE10128063A1 (de) 2001-06-09 2003-01-23 Alstom Switzerland Ltd Brennersystem
US20090173074A1 (en) * 2008-01-03 2009-07-09 General Electric Company Integrated fuel nozzle ifc
WO2011054739A2 (en) * 2009-11-07 2011-05-12 Alstom Technology Ltd Reheat burner injection system
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
EP2725302A1 (de) * 2012-10-25 2014-04-30 Alstom Technology Ltd Nachbrenneranordnung
EP3023696B1 (de) * 2014-11-20 2019-08-28 Ansaldo Energia Switzerland AG Nockenlanze für eine Gasturbinenbrennkammer
EP3026344B1 (de) * 2014-11-26 2019-05-22 Ansaldo Energia Switzerland AG Brenner einer Gasturbine
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

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Also Published As

Publication number Publication date
CN108375082A (zh) 2018-08-07
CN108375082B (zh) 2021-05-25
EP3354984A1 (de) 2018-08-01

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