EP0807213A1 - 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

Info

Publication number
EP0807213A1
EP0807213A1 EP95907643A EP95907643A EP0807213A1 EP 0807213 A1 EP0807213 A1 EP 0807213A1 EP 95907643 A EP95907643 A EP 95907643A EP 95907643 A EP95907643 A EP 95907643A EP 0807213 A1 EP0807213 A1 EP 0807213A1
Authority
EP
European Patent Office
Prior art keywords
stromungsleitkorper
shell
air
fuel
flow
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
Application number
EP95907643A
Other languages
German (de)
English (en)
Other versions
EP0807213B1 (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
BMW Rolls Royce 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 BMW Rolls Royce GmbH filed Critical BMW Rolls Royce GmbH
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

Links

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 for a gas turbine combustion chamber, which is hit by a fluid stream, which thereby experiences a change in its streamline field.
  • air atomizers are known on gas turbine combustion chambers, in particular for aircraft engines, which have two or more coaxial ring channels through which the air mass flows conveyed by the compressor flow with different swirl.
  • a mixture with fuel has already become known; two air channels are separated by a sharply tapering circular ring onto which a film of fuel is applied. This is driven by the air masses to the end edge of the annulus and atomized there. In the vicinity of the atomizing edge there is the fuel drop spray trailing character, which results in poor homogeneity of the resulting fuel-air mixture.
  • delta blades To improve the mixing processes of gases in or on gas turbine combustion chambers, so-called delta blades have also become known.
  • delta wings are sharp-edged bodies which divide an impinging flow field into two partial streams each having a vortex axis, such that the vortex axes are convergent.
  • the mixing processes that can be achieved with this cannot fully satisfy due to this convergent vortex formation.
  • the object of the invention is therefore to identify measures by means of which mixing processes of gases in gas turbine combustion chambers can be improved.
  • non-convergent and preferably divergent vertebral axes or vortex braids are to be generated downstream of the flow guide body.
  • a Stromungsleitkorper is provided, which is formed by a tapered shaped shell of substantially conical shape, the base surface pro ection is formed by a straight line and a curve connecting the end points of the straight line, and wherein the shaped shell essentially with the tip of the fluid stream occurring on the outside is facing.
  • the curve should not have any significant corner points, so that the surface of the molded shell, with the exception of the edges, has no sharp edges.
  • FIG. 1 is a perspective view of a flow guide body according to the invention (molded shell) and an impinging fluid flow,
  • FIG. 3 shows a side view of the molded shell or of the flow guide body, from which the angle of attack, the opening angle and the course of individual streamlines are evident,
  • Fig. 4 is a view from above of the molded shell or the flow guide body, the flow field of a split vortex pair is shown schematically.
  • 5 shows a so-called double-shell atomizer, essentially consisting of two flow guide bodies according to the invention
  • 6 shows the side view of such a molded shell in the region of the admixture air holes in a gas turbine combustion chamber wall
  • FIG. 8 shows a further application of a flow guide body according to the invention with a so-called fuel film layer in a side section
  • FIG. 10 shows the view Z from FIG. 8.
  • Atomizer with a fuel film layer such as
  • the flow guide body according to the invention is designated with the reference number 1 in all the figures. It is always a molded shell 1 of an essentially conical shape.
  • the projected base area 2 of this molded shell 1, the interior of which is hollow, consists of a straight line 3a and any curve 3b connecting the end points of the straight line.
  • the molded shell 1 is formed by the jacket surface which connects the curve 3b to the tip 4 of the molded shell 1.
  • the rays running from the tip 4 to the curve 3b do not have to be necessary. be straight lines, but can represent curves themselves.
  • this molded shell can be freely selected in accordance with the respective requirements, ie in a series of tests the most suitable shape of curve 3b and the most suitable value for the so-called opening angle of the through the Shaped shell 1 formed cone can be determined.
  • the best results with regard to the flow field established downstream of the flow guide body 1 were achieved if the curve 3b has no significant corner points, ie the surface of the flow guide body 1 has no other sharp edges with the exception of the marginal edges.
  • the opening angle already mentioned, which results from the structural design, is explicitly shown in FIG. 3.
  • FIG. 3 Also shown in FIG. 3 is the so-called angle of attack .beta.
  • angle of attack .beta By which the plane 5 of the shell 1 defined by the tip 4 and the straight line 3a is inclined with respect to the flow direction of the fluid flow.
  • the fluid stream striking the flow guide body or the molded shell 1 is represented by the flow vector 6.
  • the mold shell 1 is flowed against by the fluid flow 6 on its convex side, the flow lines 7 sketched in FIGS. 1, 3 being formed.
  • the vortex field shown in FIG. 2 in a section perpendicular to the main flow direction of the fluid stream 6 is formed, which vortex field has two counter-rotating vortex braids 8. Due to the design of curve 3b in particular, these two vortex braids 8 diverge downstream of the flow guide body 1, ie they diverge. In this respect, this flow control body 1 differs significantly from a delta wing known per se, which produces converging vortex braids.
  • the circulation of the pegs 8 is dependent on the angle of attack ⁇ . If the swirl is sufficiently high, the pegs 8 can burst open downstream of the molded shell 1, as is shown in FIG. 4. This forms a recirculation zone which has an inner boundary surface 9a with the main fluid flow continuing centrally. Furthermore, the fluid in rotation has an outer boundary surface 9b with the surrounding main flow fluid, which is only displaced by bending its flow lines.
  • FIG. 5 shows a preferred application for a flow guide according to the invention.
  • two molded shells 1 are arranged adjacent to one another, but spaced apart from one another, and are surrounded by a housing 10 shown broken away.
  • Each of the two molded shells 1 is adjusted by the angle of attack ⁇ relative to the horizontal, which is equal to the direction of flow of the fluid stream, in such a way that the planes 5 of these molded shells 1, which were defined in FIG. 3, are between them enclose the angle 2 ß.
  • the two shells 1 can also have a common tip 4.
  • gaseous or solid fuels can also be applied to the convex sides or outer sides of the molded shells 1, then the arrangement shown acts as a mixer with a flame holder. The flame is always stabilized by the recirculation zone explained in connection with FIG. 4 within the burst vertebrae (see reference number 8).
  • a rapid air admixture in gas turbine combustion chambers can be achieved, for example.
  • This second main stream represents the fuel gas and is drawn into the recirculation zone of the vortex braids 8.
  • the fuel gas mixes on the boundary surfaces 9a, 9b (cf. FIG. 4) with the fresh gas. 6, 7 show how a molded shell 1 according to the invention can be arranged on the combustion chamber wall of a gas turbine in order to optimally mix the intake air with the fuel gas within the combustion engine.
  • the molded shell is again designated by the reference number 1, while the combustion chamber wall bears the reference number 11.
  • the fuel gas flows according to the direction of arrow 13.
  • admixed air is to be added to this fuel gas stream 13.
  • the admixed air stream 6 is introduced as the fluid stream hitting a molded shell 1 outside the combustion chamber 12 along the combustion chamber wall 11 and can enter the combustion chamber 12 via an opening 14 in the combustion chamber wall 11.
  • the molded shell 1 is surrounded by a scoop 15 which intercepts a part of the incoming admixing air stream 6 and redirects it in the direction of the opening 14. This is the domed scoop 15 arranged on the outside of the combustion chamber wall 11 such that the opening 14 is enclosed.
  • the arrangement of this arrangement is as follows: While in the known prior art the admixture of admixed air often takes place in such a way that two or more air jets meet at a stagnation point and generate turbulence there, as a result of which hot gas slip between the air jets arises, the admixing air is swirled in an arrangement according to the invention.
  • the disadvantage of the known state of the art that the air jets split up in the stagnation point area into air bubbles which are carried along by the hot gas flow and thus mix slowly is avoided with a molded shell according to the invention which acts as a vortex generator.
  • FIGS. 8 to 10 Another application for a molded shell 1 according to the invention or a flow guide body according to the invention is shown in FIGS. 8 to 10.
  • the molded shell 1 is arranged in the flow path of two fluid streams, namely an air stream 6 and a fuel stream 20 and acts as a so-called shell air atomizer for a fuel film layer.
  • 8, 9 show, the molded shell 1 is again surrounded by a jacket-shaped scoop 15, in which the fuel film layer 21 is arranged.
  • the fuel film layer 21 has a fuel channel 22 which ends in a flat funnel 23.
  • the tray air atomizer arrangement shown is flowed against by the fluid stream 6.
  • FIG. 10 shows the view Z from FIG. 8 on the fuel film layer 21.
  • the fuel channel 22 and the flat funnel 23 can be seen.
  • the outer contour of the film layer 21 is aerodynamically shaped.
  • one or more fuel pressure atomizing nozzles with any desired spray nozzle characteristics can also be used in conjunction with a molded shell 1 (flow guide body) according to the invention. be arranged to achieve a favorable air-fuel mixture.
  • fuel is also applied to the convex side of the molded shell 1 by a pressure atomizing nozzle in analogy to the film layer.
  • FIGS. 12, 14 show further exemplary embodiments of a double-shell atomizer consisting of two molded shells 1 with a fuel film layer 21 - as an alternative, pressure atomizer nozzles can be provided .
  • 11 shows a double-shell atomizer with two molded shells, similar to FIG. 5.
  • the fuel is divided into two channels 22 (here without a flat funnel 23).
  • the flow guide body 1 according to the invention and the molded shell 1 according to the invention thus act in the last exemplary embodiments in conjunction with a fuel film applicator 21 as a shell air atomizer, the fuel being able to be supplied through one or more fuel channels 22, wherein the fuel channels 22 and possibly in one or more flat funnels 23 and the atomizer or the molded shell 1 are arranged at a short distance from the flat funnel 23 or from the mouth of the channels 22, and the film layer 21 in the plane of symmetry of the for - bowl (s) 1.
  • a flow guide body according to the invention or a molded shell 1 can also be used as a vortex generator, which then consists in particular of one or more arbitrarily shaped molded shells 1 and one or more matching scoops 15.
  • This arrangement can be used for mixing and swirling cold air in gas turbine combustion chambers.
  • This arrangement can be placed anywhere on the flame tube of any combustion chamber in any position.
  • these conical shaped shell (s) 1 of the shape shown in FIG. 1 can be of any cross-section, the rays going from the tip 4 to the base or base surface 2 of the conical section not needing to be straight lines.
  • this molded shell 1 can be used as an air atomizer for any liquid fuel.
  • it can also be used as a mixing element and flame holder when using gaseous or pulverized or granulated solid fuels of any kind.
  • any different gas or fluid streams can also be mixed with one another.
  • a large number of details, in particular of a constructive type can be designed quite differently from the exemplary embodiments shown, without departing from 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.
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 true EP0807213A1 (fr) 1997-11-19
EP0807213B1 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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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
EP0807213B1 (fr) 2002-07-31
CA2209672C (fr) 2006-06-06
CA2209672A1 (fr) 1996-08-08
DE59510303D1 (de) 2002-09-05

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