EP0807213B1 - Corps de guidage de l'ecoulement pour chambres de combustion de turbines a gaz - Google Patents

Corps de guidage de l'ecoulement pour chambres de combustion de turbines a gaz Download PDF

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Publication number
EP0807213B1
EP0807213B1 EP95907643A EP95907643A EP0807213B1 EP 0807213 B1 EP0807213 B1 EP 0807213B1 EP 95907643 A EP95907643 A EP 95907643A EP 95907643 A EP95907643 A EP 95907643A EP 0807213 B1 EP0807213 B1 EP 0807213B1
Authority
EP
European Patent Office
Prior art keywords
fuel
shell
flow
combustion chamber
air
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.)
Expired - Lifetime
Application number
EP95907643A
Other languages
German (de)
English (en)
Other versions
EP0807213A1 (fr
Inventor
Achim Schmid
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.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
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 Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP0807213A1 publication Critical patent/EP0807213A1/fr
Application granted granted Critical
Publication of EP0807213B1 publication Critical patent/EP0807213B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
    • B01F—MIXING, e.g. DISSOLVING, EMULSIFYING OR DISPERSING
    • B01F25/00—Flow mixers; Mixers for falling materials, e.g. solid particles
    • B01F25/40—Static mixers
    • B01F25/42—Static mixers in which the mixing is affected by moving the components jointly in changing directions, e.g. in tubes provided with baffles or obstructions
    • B01F25/43—Mixing tubes, e.g. wherein the material is moved in a radial or partly reversed direction
    • B01F25/431—Straight mixing tubes with baffles or obstructions that do not cause substantial pressure drop; Baffles therefor
    • B01F25/43197—Straight mixing tubes with baffles or obstructions that do not cause substantial pressure drop; Baffles therefor characterised by the mounting of the baffles or obstructions
    • B01F25/431971—Mounted on the wall
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15D—FLUID DYNAMICS, i.e. METHODS OR MEANS FOR INFLUENCING THE FLOW OF GASES OR LIQUIDS
    • F15D1/00—Influencing flow of fluids
    • F15D1/0005—Baffle plates
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15D—FLUID DYNAMICS, i.e. METHODS OR MEANS FOR INFLUENCING THE FLOW OF GASES OR LIQUIDS
    • F15D1/00—Influencing flow of fluids
    • F15D1/02—Influencing flow of fluids in pipes or conduits
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M9/00—Baffles or deflectors for air or combustion products; Flame shields
    • F23M9/02—Baffles or deflectors for air or combustion products; Flame shields in air inlets
    • 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
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
    • F23R3/20—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants incorporating fuel injection means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2209/00—Safety arrangements
    • F23D2209/20—Flame lift-off / stability
    • 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
    • F23D2900/11101—Pulverising gas flow impinging on fuel from pre-filming surface, e.g. lip atomizers

Definitions

  • the invention relates to a flow guide body on a gas turbine combustion chamber for swirling an impinging air flow, consisting of at least one tapered molded shell of essentially conical shape, the base surface projection of which is formed by at least one straight line and any curve connecting the end points of the straight line, wherein the tip of the molded shell essentially faces the air flow hitting the outside.
  • a comparable flow guide body is known from EP-A-0 063 729 as a device for inverting and mixing flowing substances.
  • Air atomizers known which have two or more coaxial ring channels, through which the air mass flows conveyed by the compressor with different Stream swirl. It became known in this context already a mixture with fuel; there are two air channels separated by a tapered circular ring on which a fuel film is applied. This is from the air masses to the end edge of the Driven circular ring and atomized there. In the vicinity of the atomizing edge has the fuel drop spray trailing character, what a poor homogeneity of the resulting air-fuel mixture results.
  • delta wings To improve the mixing processes of gases in or on gas turbine combustion chambers so-called delta wings have also become known. For this purpose, reference is made, for example, to EP 0 623 786 A1 or to US 3,974,646. Delta wings of this type are sharp-edged Bodies that have an impinging flow field in two each a vortex axis divides possessing partial flows in such a way that the vortex axes run convergent. The mixing processes that can be achieved hereby can be convergent Do not fully satisfy vortex formation.
  • the object of the invention is therefore to demonstrate measures by means of which mixing processes of gases in gas turbine combustion chambers can be improved.
  • non-convergent and preferably divergent vortex axes or vortex braids are to be generated downstream of the flow guide body.
  • the so-called flow guide is in all the figures designated with the reference number 1. It is always a Shaped shell 1 of substantially conical shape.
  • the projected Base 2 of this molded shell 1, the interior of which is hollow, is made from a straight line 3a as well as any one, the end points of the straight line connecting curve 3b.
  • the molded shell 1 is formed by the Shell surface, which connects the curve 3b with the tip 4 of the molded shell 1. However, those running from tip 4 to curve 3b must Rays not necessarily Be straight, but can even curves represent.
  • the shape of this molded shell is the respective one Freely selectable requirements accordingly, d. H.
  • the circulation of the pegs 8 is from Angle of attack depends on ⁇ . With a sufficiently high swirl the pegs 8 burst open downstream of the molded shell 1, as shown in Fig. 4. It forms a recirculation zone which has an inner interface 9a to the central main flow of fluid. Further the fluid in rotation has one outer interface 9b to the surrounding main flow fluid, which only displaces under the curvature of its streamlines becomes.
  • FIG. 5 A preferred application for an inventive Flow guide body shows Fig. 5.
  • each other adjacent, but spaced apart, two molded shells 1 arranged by a broken open Housing 10 are surrounded.
  • Each of the two molded shells 1 is the angle of attack ⁇ relative to the horizontal, which is equal to the direction of flow of the fluid stream be employed in such a way that levels 5 of these Shells 1, which were defined in Fig. 3, between enclose the angle 2 ⁇ .
  • So-called double-shell atomizer which is essentially from two flow guide bodies 1 according to the invention is an air atomizer with a flame holder, where liquid fuel makes sense on the convex Side of the two molded shells 1 is applied.
  • gaseous or solid fuels can also be used also on the convex sides or outer sides of the Shells 1 are applied, then the one shown acts Arrangement as a mixer with flame holder. Always there a stabilization of the flame through the connection 4 illustrated recirculation zone within the split vertebrae (see reference number 8) reached.
  • the eddy current field of the molded shell 1 or molded shells 1 perpendicular to a second main stream is quick, for example Air admixture can be achieved in gas turbine combustion chambers.
  • This second main stream represents the fuel gas and is sucked into the recirculation zone of the vortex braids 8.
  • the fuel gas mixes at the interfaces 9a, 9b (see FIG. 4) with the fresh gas.
  • a gas turbine can be arranged to the admixing air optimal with the fuel gas inside the combustion chamber 6, 7 show how to mix.
  • the molded shell is again with the reference number 1 denotes while the combustion chamber wall Reference number 11 carries.
  • the fuel gas flows according to Arrow direction 13.
  • This fuel gas stream 13 should be like known admixture air can be added.
  • the admixed air flow 6 as the one hitting a molded shell 1 Fluid flow outside of the combustion chamber 12 along the Combustion chamber wall 11 brought up and can Opening 14 in the combustion chamber wall 11 in the combustion chamber 12 occur.
  • the molded shell 1 surrounded by a scoop 15, which is part of the incoming Mixing air flow 6 intercepts and in the direction of Breakthrough 14 redirects. This is the domed scoop 15 arranged on the outside of the combustion chamber wall 11 in such a way that the opening 14 is included.
  • the cold admixing air 17 forms with the Fuel gas stream 13 again has an outer interface 9b.
  • the admixing air 17 is strongly swirled and compared to that Fuel gas 13 has a high density, it comes from centrifugal and buoyancy forces in the area of this interface 9b to a rapid and intensive rearrangement of both Air masses that lead to fine-grained turbulence and rapid mixing to lead.
  • the surface of the interface 9b is around many times larger than that at the previous status technology-forming surface between hot gas and admixing air. The hot gas slip through the admixing level thereby greatly reduced.
  • FIGS. 8-10 Another application for an inventive Shaped shell 1 or a flow guide body according to the invention is shown in Figs. 8-10.
  • the molded shell 1 in the flow path of two fluid flows namely an air flow 6 and a fuel flow 20 arranged and acts as a so-called shell air atomizer for a fuel film layer.
  • the molded shell 1 is again from one surrounded in the form of a hood 15 in which the fuel film layer 21 is arranged.
  • the fuel film layer 21 has a fuel channel 22 which in one Flat funnel 23 ends.
  • FIG. 10 shows the view Z from FIG. 8 of the fuel film layer 21.
  • the fuel channel 22 can be seen as well as the flat funnel 23.
  • the outer contour makes sense of the film layer 21 as can be seen aerodynamically shaped.
  • 11 shows a double-sided load Double-shell atomizer with two molded shells, similar Fig. 5.
  • the Fuel on two channels 22 here without flat funnel 23
  • the flow guide body 1 according to the invention or the one according to the invention Shaped shell 1 act in the last explained Exemplary embodiments in connection with a Fuel film layer 21 as a shell air atomizer, wherein the fuel through one or more fuel channels 22 can be supplied, the fuel channels 22 and possibly in one or more Flat funnels 23 open and the atomizer or Shaped shell 1 at a short distance from the flat funnel 23 or is arranged from the mouth of the channels 22, and the film layer 21 in the plane of symmetry of the molded shell (s) 1 lies.
  • an inventive Flow guide body or a molded shell 1 also as a vortex generator are used, which then in particular one or more arbitrarily shaped molded shells 1 as well as one or more matching scoops 15 consists.
  • This arrangement can be used for admixing and swirling cold air in gas turbine combustors.
  • This arrangement can be anywhere on the flame tube of any combustion chamber in any Location can be attached.
  • this molded shell 1 as an air atomizer used for any liquid fuel become. But it is also used as a mixing element and flame holder when using gaseous or powdered or granulated solid fuels any Kind possible.
  • any number of different ones can of course also be used Gas or fluid flows mixed together become.
  • a variety of details in particular constructive type quite different from the shown Embodiments can be designed without the Leave the content of the claims.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Dispersion Chemistry (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)
  • Spray-Type Burners (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)

Abstract

Un corps de guidage de l'écoulement est constitué d'une pièce moulée (1) en forme de coquille qui se termine en pointe et de forme sensiblement conique. La projection de sa surface de base est formée par une ligne droite (3a) et par une ligne courbe quelconque (3b) qui relie les extrémités de la ligne droite. La ligne courbe (3b) ne présente aucun angle aigu. La coquille moulée (1) fait face avec sa pointe (4) au courant de fluide qui s'écoule sur sa face extérieure et peut être utilisée comme élément mélangeur de carburant gazeux et d'air, comme atomiseur d'air à stabilisateur de flamme, comme élément mélangeur d'air apporté à des chambres de combustion, comme générateur de tourbillons ou comme atomiseur d'air à surface convexe associé à un générateur de film de carburant ou à une buse d'atomisation sous pression de carburant.

Claims (4)

  1. Organe de guidage d'écoulement pour une chambre de combustion d'une turbine à gaz destiné à mettre en rotation une veine d'air (6), composé d'au moins une coupelle (1) se terminant par un sommet ayant essentiellement une forme conique dont la projection de la surface de base (2) est délimitée par au moins une droite (3a) ainsi qu'une courbe quelconque (3b) reliant les extrémités de la droite (3a), le sommet (4) de la coupelle (1) étant tourné principalement vers la veine d'air (6) qui arrive sur la face extérieure,
    caractérisé en ce que
    la coupelle (1) est entourée par un capot (15) et elle est prévue sur le côté extérieur de la paroi (11) de la chambre de combustion de sorte que le passage entouré par le capot (15) mélange la veine d'air froid (6) à la veine de gaz combustible (13) passant dans la chambre de combustion (12).
  2. Organe de guidage d'écoulement pour une chambre de combustion d'une turbine à gaz, pour mettre en rotation une veine d'air d'entrée (6), composé d'au moins une coupelle (1) se terminant par un sommet et ayant une forme essentiellement conique dont la projection de la surface de base (2) est formée par au moins une droite (3a) et une courbe quelconque (3b) qui relie les extrémités de la droite (3a), la coupelle (1) ayant son sommet (4) tourné essentiellement contre la veine d'air (6) arrivant sur la face extérieure,
    caractérisé en ce que
    la coupelle (1) est entourée d'un capot (15) et est combinée avec un injecteur de film de carburant (21) ou une buse de pulvérisation de carburant sous pression,
    le carburant arrivant sur la face extérieure de la coupelle (1) pour être fourni en commun avec la veine d'air (6) à la chambre de combustion.
  3. Organe de guidage d'écoulement selon l'une quelconque des revendications 1 ou 2,
    caractérisé en ce que
    le plan (5) de la coupelle (1) passant par le sommet (4) et la droite (3a) est inclinée par rapport à la direction de passage de la veine d'air (6) (angle d'inclinaison β).
  4. Organe de guidage d'écoulement selon l'une quelconque des revendications précédentes,
    caractérisé en ce que
    plusieurs coupelles (1) sont installées au voisinage les unes des autres mais sont toutefois au moins écartées les unes des autres par zone à l'intérieur d'un boítier commun (10).
EP95907643A 1995-02-03 1995-02-03 Corps de guidage de l'ecoulement pour chambres de combustion de turbines a gaz Expired - Lifetime EP0807213B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/EP1995/000401 WO1996023981A1 (fr) 1995-02-03 1995-02-03 Corps de guidage de l'ecoulement pour chambres de combustion de turbines a gaz

Publications (2)

Publication Number Publication Date
EP0807213A1 EP0807213A1 (fr) 1997-11-19
EP0807213B1 true EP0807213B1 (fr) 2002-07-31

Family

ID=8165953

Family Applications (1)

Application Number Title Priority Date Filing Date
EP95907643A Expired - Lifetime EP0807213B1 (fr) 1995-02-03 1995-02-03 Corps de guidage de l'ecoulement pour chambres de combustion de turbines a gaz

Country Status (5)

Country Link
US (1) US5918465A (fr)
EP (1) EP0807213B1 (fr)
CA (1) CA2209672C (fr)
DE (1) DE59510303D1 (fr)
WO (1) WO1996023981A1 (fr)

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US6971239B2 (en) * 2003-05-13 2005-12-06 United Technologies Corporation Augmentor pilot nozzle
US7140184B2 (en) * 2003-12-05 2006-11-28 United Technologies Corporation Fuel injection method and apparatus for a combustor
DE102004015904A1 (de) * 2004-03-31 2005-10-20 Alstom Technology Ltd Baden Verfahren zur Flüssigbrennstoffzerstäubung in einem Vormischbrenner sowie Vormischbrenner
US8746965B2 (en) * 2007-09-07 2014-06-10 Turbulent Energy, Llc Method of dynamic mixing of fluids
US9144774B2 (en) * 2009-09-22 2015-09-29 Turbulent Energy, Llc Fluid mixer with internal vortex
US9310076B2 (en) 2007-09-07 2016-04-12 Turbulent Energy Llc Emulsion, apparatus, system and method for dynamic preparation
US9708185B2 (en) * 2007-09-07 2017-07-18 Turbulent Energy, Llc Device for producing a gaseous fuel composite and system of production thereof
US8715378B2 (en) 2008-09-05 2014-05-06 Turbulent Energy, Llc Fluid composite, device for producing thereof and system of use
US8871090B2 (en) 2007-09-25 2014-10-28 Turbulent Energy, Llc Foaming of liquids
JP2009081301A (ja) * 2007-09-26 2009-04-16 Toyo Tanso Kk 太陽電池ユニット
US8844495B2 (en) 2009-08-21 2014-09-30 Tubulent Energy, LLC Engine with integrated mixing technology
US8863525B2 (en) 2011-01-03 2014-10-21 General Electric Company Combustor with fuel staggering for flame holding mitigation
US9228747B2 (en) * 2013-03-12 2016-01-05 Pratt & Whitney Canada Corp. Combustor for gas turbine engine
US9797601B2 (en) 2015-01-21 2017-10-24 United Technologies Corporation Bluff body fuel mixer
CN106994305B (zh) * 2017-03-31 2023-10-03 浙江理工大学 可调进气泡大小的气液混合装置
CN115771995B (zh) * 2022-12-30 2024-09-10 重庆鑫景特种玻璃有限公司 一种浮法玻璃锡槽吹扫装置

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Also Published As

Publication number Publication date
US5918465A (en) 1999-07-06
WO1996023981A1 (fr) 1996-08-08
EP0807213A1 (fr) 1997-11-19
CA2209672C (fr) 2006-06-06
CA2209672A1 (fr) 1996-08-08
DE59510303D1 (de) 2002-09-05

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