EP0807213A1 - Flow-guiding body for gas turbine combustion chambers - Google Patents

Flow-guiding body for gas turbine combustion chambers

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)
French (fr)
Other versions
EP0807213B1 (en
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/en
Application granted granted Critical
Publication of EP0807213B1 publication Critical patent/EP0807213B1/en
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)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
  • Spray-Type Burners (AREA)

Abstract

A flow-guiding body is designed as a pointed, substantially conical moulded shell (1). The projection of its base surface is formed by a straight line (3a) and by a curve (3b) that interconnects the ends of the straight line. The curve (3b) forms no significant angles. The moulded shell (1) faces with its point the fluid flow that hits its outer side and may be used as a mixing element for gaseous fuel and air, as an air sprayer with flame-holder, as a mixing element for admixed air in combustion chambers, as a swirling element or as a shell-shaped air sprayer combined with a fuel film generator or a fuel pressure spraying nozzle.

Description

Stromungsleitkorper für eine Gasturbinen-BrennkammerFlow control body for a gas turbine combustion chamber
Die Erfindung betrifft einen Stromungsleitkorper für eine Gasturbinen-Brennkammer, auf den ein Fluidstrom auf¬ trifft, der hierdurch eine Veränderung seines Strom¬ linienfeldes erfährt. An Gasturbinen-Brennkammern insbe¬ sondere für Flugtriebwerke sind sog. Luftzerstauber be¬ kannt, die zwei oder mehrere koaxiale Ringkanäle be- sitzen, durch die die vom Verdichter geförderten Luftmas¬ senströme mit unterschiedlichem Drall strömen. Bekannt wurde in diesem Zusammenhang bereits auch eine Vermengung mit Kraftstoff; dabei sind zwei Luftkanale durch einen scharf zulaufenden Kreisring getrennt, auf den ein Kraft- stoffilm aufgebracht wird. Dieser wird dabei von den Luftmassen zur Endkante des Kreisringes getrieben und dort zerstäubt. Im Nahbereich der Zerstäubungskante be¬ sitzt dabei das Kraftstoff-Tropfenspray Nachlaufcharak¬ ter, was eine schlechte Homogenitat des entstehenden Kraftstoff-Luft-Gemisches ergibt.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. So-called 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. In this context, 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.
Weiterhin ist es an Gasturbinen bekannt, die Zumischluft für die verschiedenen Brennzonen einer Brennkammer durch gedruckte oder gebohrte Locher in der Brennkammerwand zu- zufuhren. Dies geschieht häufig derart, daß sich die ein¬ zelnen Luftstrahlen, die durch verschiedene Locher in der Brennkammerwand gelangen, in einem Staupunkt treffen und dort lokal für hohe Turbulenz sorgen. Dabei werden die eingeblasenen Luftstrahlen im Inneren der Brennkammer vom dort befindlichen Heißgas jedoch in der Art eines massi- ven Stabes umströmt, so daß sich im Bereich des Zusammen¬ treffens von Heißgas und Zu ischluft keine optimale Luft¬ vermischung ergibt. Lediglich im Grenzschichtbereich zwi¬ schen dem Zumisch-Luftstrahl und dem Heißgas tritt eine Mischung auf. Dieser sog. Heißgasschlupf durch den Loch- querschnitt einer Brennkammer ist bekanntermaßen relativ hoch.It is also known in gas turbines to supply the admixing air for the various combustion zones to a combustion chamber through printed or drilled holes in the wall of the combustion chamber. This often happens in such a way that the individual air jets that pass through different holes in the Coming to the combustion chamber wall, meeting at a stagnation point and ensuring high turbulence locally. In this case, however, the hot gas located there flows around the blown-in air jets in the interior of the combustion chamber in the manner of a solid rod, so that there is no optimal air mixing in the area where hot gas and intake air meet. A mixture occurs only in the boundary layer area between the admixing air jet and the hot gas. This so-called hot gas slip through the hole cross section of a combustion chamber is known to be relatively high.
Zur Verbesserung der Mischprozesse von Gasen in oder an Gasturbinen-Brennkammern sind ferner bereits sog. Delta- Flügel bekannt geworden. Verwiesen wird hierzu beispiels¬ weise auf die EP 0 623 786 AI oder auf die US 3,974,646. Bei derartigen Delta-Flugeln handelt es sich um scharf¬ kantige Korper, die ein auftreffendes Stromungsfeld in zwei jeweils eine Wirbelachse besitzende Teilstrome auf- teilt, derart, daß die Wirbelachsen konvergent verlaufen. Die hiermit erzielbaren Mischprozesse können aufgrund dieser konvergenten Wirbelbildung nicht voll befriedigen.To improve the mixing processes of gases in or on gas turbine combustion chambers, so-called delta blades have also become known. For this purpose, reference is made, for example, to EP 0 623 786 AI or to US 3,974,646. Such 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.
Aufgabe der Erfindung ist es daher, Maßnahmen aufzuzei- gen, mit Hilfe derer Mischprozesse von Gasen in Gasturbi¬ nen-Brennkammern verbessert werden können. Insbesondere sollen nicht konvergente und bevorzugt divergent verlau¬ fende Wirbelachsen bzw. Wirbelzopfe stromab des Stro- ungsleitkorpers erzeugt werden. Zur Losung dieser Aufgabe ist ein Stromungsleitkorper vorgesehen, der durch eine spitz zulaufende Formschale von im wesentlichen kegelförmiger Gestalt gebildet wird, wobei die Grundflächen-Pro ektion durch eine Gerade sowie eine die Endpunkte der Geraden verbindende Kurve gebildet ist, und wobei die Formschale im wesentlichen mit ihrer Spitze dem auf der Außenseite auftre fenden Fluidstrom zugewandt ist. Insbesondere soll die Kurve keine signifi¬ kanten Eckpunkte aufweisen, so daß die Oberfläche der Formschale mit Ausnahnme der Ränder keine scharfen Kanten besitzt.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. In particular, non-convergent and preferably divergent vertebral axes or vortex braids are to be generated downstream of the flow guide body. To solve this problem, 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. In particular, 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.
Vorteilhafte Aus- und Weiterbildungen sind Inhalt der Un¬ teransprüche, weiterhin wird in Unteransprüchen Schutz begehrt für eine Gasturbine mit zumindest einem in beson¬ derer Weise angeordneten erfindungsgemäßen Strömungsleit¬ körper.Advantageous training and further developments are the content of the subclaims, furthermore protection is sought in the subclaims for a gas turbine with at least one flow guide body according to the invention arranged in a special way.
Näher erläutert wird die Erfindung anhand bevorzugter Ausführungsbeispiele. Im einzelnen zeigtThe invention is explained in more detail with reference to preferred exemplary embodiments. In detail shows
Fig. 1 eine Perspektivdarstellung eines erfindungsge- mäßen Strömungsleitkörpers (Formschale) sowie einen auftreffenden Fluidstrom,1 is a perspective view of a flow guide body according to the invention (molded shell) and an impinging fluid flow,
Fig. 2 das von der Formschale induzierte Strömungs¬ wirbelfeld in einem Schalenschnitt senkrecht zur Hauptstromrichtung,2 the vortex field induced by the molded shell in a shell section perpendicular to the main flow direction,
Fig. 3 eine Seitenansicht der Formschale bzw. des Strömungsleitkörpers, aus der der Anstellwin¬ kel, der Öffnungswinkel sowie der Verlauf ein- zelner Stromlinien hervorgeht,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 einen Blick von oben auf die Formschale bzw. den Strömungsleitkörper, wobei schematisch das Strömungsfeld eines aufgeplatzten Wirbelpaares dargestellt ist.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.
Fig. 5 zeigt einen sog. Doppelschalenzerstäuber, im wesentlichen bestehend aus zwei erfindungsge¬ mäßen Strömungsleitkörpern, Fig. 6 zeigt die Seitenansicht einer derartigen Form¬ schale im Bereich der Zumisch-Luftlocher einer Gasturbinen-Brennkammerwand,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. 7 die Ansicht X aus Fig. 6,7 shows the view X from FIG. 6,
Fig. 8 eine weitere Anwendung eines erfindungsgemaßen Stromungsleitkorpers mit einem sog. Kraftstoff- Filmleger in einem Seitenschnitt,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. 9 die Ansicht Y aus Fig. 8, sowieFig. 9, the view Y of Fig. 8, as well
Fig. 10 die Ansicht Z aus Fig. 8.10 shows the view Z from FIG. 8.
Fig. 11 eine andere Ausgestaltung mit einem Kraftstoff- Filmleger,11 shows another embodiment with a fuel film layer,
Fig. 12 den Schnitt A-A aus Fig. 11,12 shows the section A-A from FIG. 11,
Fig. 13 noch eine weitere Variante eines Doppelschalen-13 is yet another variant of a double-shell
Zerstaubers mit einem Kraftstoff-Filmleger, so¬ wieAtomizer with a fuel film layer, such as
Fig. 14 den Schnitt B-B aus Fig. 1314 shows section B-B from FIG. 13
In samtlichen Figurendarstellungen ist der erfindungsge- maße Stromungsleitkorper mit der Bezugsziffer 1 bezeich¬ net. Dabei handelt es sich stets um eine Formschale 1 von im wesentlichen kegelförmiger Gestalt. Die projezierte Grundflache 2 dieser Formschale 1, deren Inneres hohl ausgebildet ist, besteht aus einer Geraden 3a sowie einer beliebigen, die Endpunkte der Geraden verbindenden Kurve 3b. Gebildet wird die Formschale 1 dabei durch die Mantelflache, die die Kurve 3b mit der Spitze 4 der Form- schale 1 verbindet. Dabei müssen jedoch die von der Spitze 4 zur Kurve 3b verlaufenden Strahlen nicht notwen- digerweise Geraden sein, sondern können selbst Kurven darstellen. Die Gestalt dieser Formschale ist den jewei¬ ligen Anforderungen entsprechend frei wählbar, d. h. in einer Versuchsreihe kann für den jeweiligen Anwendungs- zweck dieses erfindungsgemäßen Strömungsleitungkörpers die jeweils geeignetste Form der Kurve 3b sowie der je¬ weils geeignetste Wert für den sog. όffnungswinkel des durch die Formschale 1 gebildeten Kegels bestimmt werden. Beste Ergebnisse im Hinblick auf das sich einstellende Strömungsfeld stromab des Strömungsleitkörpers 1 wurden dabei erzielt, wenn die Kurve 3b keine signifikanten Eck¬ punkte besitzt, d. h. die Oberfläche des Strömungsleit¬ körpers 1 besitzt mit Ausnahme der Randkanten keine son¬ stigen scharfen Kanten. Der bereits zitierte, sich durch die konstruktive Gestaltung ergebende Öffnungswinkel ist in Fig. 3 explizit dargestellt.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. However, 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. The shape of 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.
Ebenfalls Fig. 3 entnehmbar ist der sog. Anstellwinkel ß, um den die durch die Spitze 4 sowie die Gerade 3a defi- nierte Ebene 5 der For schale 1 gegenüber der An¬ strömrichtung des Fluidstromes geneigt ist. Der auf den Strömungsleitkörper bzw. die Formschale 1 auftreffende Fluidstro ist dabei durch den Strömungsvektor 6 darge¬ stellt. Wie ersichtlich wird die Formschale 1 vom Fluid- ström 6 auf ihrer konvexen Seite angeströmt, wobei sich die in den Fig. 1, 3 skizzierten Stromlinien 7 ausbilden.Also shown in FIG. 3 is the so-called 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. As can be seen, 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.
Auf der konkaven Seite der Formschale 1 bildet sich das in Fig. 2 in einem Schnitt senkrecht zur Hauptstromrich- tung des Fluidstromes 6 dargestellte Wirbelfeld aus, wel¬ ches zwei gegenläufig drehende Wirbelzopfe 8 besitzt. Aufgrund der Gestaltung insbesondere der Kurve 3b laufen diese beiden Wirbelzopfe 8 stromab des Stromungsleitkör¬ pers 1 auseinander, d. h. sie divergieren. Insofern un- terscheidet sich dieser Stromungsleitkorper 1 wesentlich von einem an sich bekannten Delta-Flugel, der konvergie¬ rende Wirbelzöpfe erzeugt.On the concave side of the molded shell 1, 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.
Die Zirkulation der Wirbelzopfe 8 ist dabei vom Anstellwinkel ß abhangig. Bei genügend hohem Drall können die Wirbelzopfe 8 stromab der Formschale 1 aufplatzen, wie dies in Fig. 4 dargestellt ist. Dabei bildet sich eine Rezirkulationszone, die eine innere Grenzflache 9a zum zentral weiterlaufenden Hauptfluidstrom besitzt. Fer- ner besitzt das sich in Drehung befindliche Fluid eine äußere Grenzfläche 9b zum umgebenden Hauptstromfluid, welches lediglich unter Krümmung seiner Stromlinien ver¬ drangt wird.The circulation of the pegs 8 is dependent on the angle of attack β. 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.
Einen bevorzugten Anwendungsfall für einen erfindungsge- maßen Stromungsleitkorper zeigt Fig. 5. Hier sind einan¬ der benachbart, jedoch voneinander beabstandet zwei Form¬ schalen 1 angeordnet, die von einem aufgebrochen darge¬ stellten Gehäuse 10 umgeben sind. Jede der beiden Form- schalen 1 ist um den Anstellwinkel ß gegenüber der Hori¬ zontalen, die gleich der Stromungsrichtung des Fluidstro¬ mes sei, angestellt, derart, daß die Ebenen 5 dieser Formschalen 1, die in Fig. 3 definiert wurden, zwischen sich den Winkel 2 ß einschließen. Dieser in Fig. 5 ge- zeigte sog. Doppelschalenzerstauber, der somit im wesent¬ lichen aus zwei erfindungsgemaßen Stromungsleitkorpern 1 besteht, stellt einen Luftzerstauber mit Flammhalter dar, wobei flussiger Kraftstoff sinnvollerweise auf die kon¬ vexe Seite der beiden Formschalen 1 aufgebracht wird. Die Strömung bildet sich wie gewünscht auf der Ruckseite der Formschalen 1 aus, wobei der Fluidstrom zwischen diesen Formschalen 1 durch das durch den Winkel 2ß beschriebene Winkelsegment im wesentlichen linksseitig sowie rechts¬ seitig der Symmetrielinie der Formschalen hindurchtritt. Dabei können abweichend von der gezeigten Anordnung die beiden Schalen 1 auch eine gemeinsame Spitze 4 besitzen. Im übrigen können auch gasformige oder feste Kraftstoffe ebenfalls auf die konvexen Seiten bzw. Außenseiten der Formschalen 1 aufgebracht werden, dann wirkt die gezeigte Anordnung als Mischer mit Flammhalter. Stets wird dabei eine Stabilisierung der Flamme durch die in Verbindung mit Fig. 4 erläuterte Rezirkulationszone innerhalb der aufgeplatzten Wirbelzopfe (vgl. Bezugsziffer 8) erreicht.FIG. 5 shows a preferred application for a flow guide according to the invention. Here, 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 β 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. This so-called double-shell atomizer shown in FIG. 5, which thus essentially consists of two flow guide bodies 1 according to the invention, represents an air atomizer with a flame holder, liquid fuel being expediently applied to the convex side of the two molded shells 1. The flow is formed as desired on the rear side of the molded shells 1, the fluid flow between these molded shells 1 passing through the angle segment described by the angle 2ß essentially on the left side and on the right side of the line of symmetry of the molded shells. In a departure from the arrangement shown, the two shells 1 can also have a common tip 4. In addition, 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).
Wird dabei zusatzlich das Wirbelstromfeld der Formschale 1 bzw. Formschalen 1 senkrecht zu einem zweiten Haupt¬ strom gestellt, so ist damit beispielsweise eine rasche Luftzumischung in Gasturbinen-Brennkammern erzielbar. Dieser zweite Hauptstrom stellt dabei das Brenngas dar und wird in die Rezirkulationszone der Wirbelzopfe 8 ein- gesogen. Dabei vermischt sich das Brenngas auf den Grenz¬ flachen 9a, 9b (vgl. Fig. 4) mit dem Frischgas. Wie dabei eine erfindungsgemaße Formschale 1 auf der Brennkammer¬ wand einer Gasturbine angeordnet sein kann, um die Zu- ischluft optimal mit dem Brenngas innerhalb der Brenn- kam er zu vermischen, zeigen die Fig. 6, 7.If, in addition, the eddy current field of the molded shell 1 or molded shells 1 is placed perpendicular to a second main stream, 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.
In den Fig. 6, 7 ist die Formschale abermals mit der Be¬ zugsziffer 1 bezeichnet, wahrend die Brennkammerwand die Bezugsziffer 11 tragt. Innerhalb der von der Brennkammer- wand 11 begrenzten Brennkammer 12 strömt das Brenngas ge¬ mäß Pfeilrichtung 13. Diesem Brenngas-Strom 13 soll wie bekannt Zumischluft beigefugt werden. Dabei wird der Zu- mischluft-Strom 6 als der auf eine Formschale 1 auftref¬ fende Fluidstrom außerhalb der Brennkammer 12 entlang der Brennkammerwand 11 herangeführt und kann über einen Durchbruch 14 in der Brennkammerwand 11 in die Brennkam¬ mer 12 eintreten. Um dabei die gewünschte Strömung des Zumischluft-Stro es 6 zu erzielen, ist die Formschale 1 von einer Hutze 15 umgeben, die einen Teil des ankommen- den Zumischluft-Stromes 6 abfangt und in Richtung des Durchbruches 14 umleitet. Hierzu ist die gewölbte Hutze 15 auf der Außenseite der Brennkammerwand 11 derart ange¬ ordnet, daß der Durchbruch 14 eingeschlossen wird.6, 7, the molded shell is again designated by the reference number 1, while the combustion chamber wall bears the reference number 11. Within the combustion chamber 12 delimited by the combustion chamber wall 11, the fuel gas flows according to the direction of arrow 13. As is known, 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. In order to achieve the desired flow of the admixing air stream 6, 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.
Der Zwecx dieser Anordnung ist der folgende: Während beim bekannten Stand der Technik die Beimengung von Zu- mischluft häufig so geschieht, daß sich zwei oder mehrere Luftstrahlen in einem Staupunkt treffen und dort Turbu¬ lenz erzeugen, wodurch ein starker Heißgasschlupf zwi¬ schen den Luftstrahlen entsteht, wird bei einer erfin- dungsgemäßen Anordnung die Zumischluft verdrallt. Der beim bekannten Stand der Technik vorliegende Nachteil, daß sich die Luftstrahlen im Staupunktbereich in Luftbla¬ sen aufspalten, die vom Heißgasstrom mittransportiert werden und sich somit langsam ausmischen, wird mit einer erfindungsgemäßen Formschale, die als Wirbelgenerator wirkt, vermieden. Wie bereits erläutert, werden nämlich auch hier mit dieser Formschale 1 Wirbelzöpfe 8 erzeugt, die bei genügend hohem Drall aufplatzen, wodurch sich das in Fig. 6 dargestellte Strömungsfeld mit der Re- Zirkulationszone 16 ausbildet, die von der Zumischluft 17 umgeben ist. Die Verbesserung der Mischwirkung gegenüber dem bekannten Stand der Technik wird dabei durch folgende Effekte erreicht: Die kalte Zumischluft 17 bildet mit dem Brenngas-Strom 13 wieder eine äußere Grenzfläche 9b. Da die Zumischluft 17 stark verdrallt ist und gegenüber dem Brenngas 13 eine hohe Dichte besitzt, kommt es durch Zen¬ trifugal- und Auftriebskräfte im Bereich dieser Grenzflä¬ che 9b zu einer raschen und intensiven Umlagerung beider Luftmassen, die zu feinkörniger Turbulenz und rascher Mi- schung führen. Die Oberfläche der Grenzfläche 9b ist um ein vielfaches größer als die sich beim bisherigen Stand der Technik bildende Oberfläche zwischen Heißgas und Zu¬ mischluft. Der Heißgasschlupf durch die Zumischebene wird dadurch stark verringert. Ein weiterer Anwendungsfall für eine erfindungsgemaße Formschale 1 bzw. einen erfindungsgemaßen Stromungsleit¬ korper ist in den Fig. 8 bis 10 dargestellt. Auch hierbei ist die Formschale 1 im Strömungsweg zweier Fluidstrome, nämlich eines Luftstromes 6 sowie eines Kraftstoffstromes 20 angeordnet und wirkt dabei als sog. Schalenluftzer¬ stäuber für einen Kraftstoff-Filmleger. Wie die Fig. 8, 9 zeigen, ist dabei die Formschale 1 abermals von einer mantelformigen Hutze 15 umgeben, in der der Kraftstoff- Filmleger 21 angeordnet ist. Der Kraftstoff-Filmleger 21 besitzt dabei einen Kraftstoffkanal 22, der in einem Flachtrichter 23 endet. Wie bereits in den vorherigen An¬ wendungsbeispielen auch wird die gezeigte Schalenluftzer- stauberanordnung vom Fluidstro 6 angeströmt.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. As already explained, with this molded shell 1, vortex braids 8 are produced which burst when the swirl is sufficiently high, as a result of which the flow field shown in FIG. 6 is formed with the recirculation zone 16, which is surrounded by the admixing air 17. The improvement in the mixing effect compared to the known prior art is achieved by the following effects: The cold admixing air 17 again forms an outer interface 9b with the fuel gas stream 13. Since the admixing air 17 is strongly swirled and has a high density compared to the fuel gas 13, centrifugal and buoyant forces in the area of this interface 9b result in a rapid and intensive rearrangement of both air masses, which leads to fine-grained turbulence and rapid mixing. lead. The surface of the interface 9b is many times larger than the surface formed between hot gas and admixed air in the prior art. The hot gas slip through the admixing level is thereby greatly reduced. 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. Here, too, 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. As already in the previous application examples, the tray air atomizer arrangement shown is flowed against by the fluid stream 6.
Für die Funktion des Kraftstoff-Filmlegers 21 ist es wichtig, daß dieser wie in Fig. 9 gezeigt, in der Symme¬ trieachse der Formschale 1 liegt. Desweiteren ist es wichtig, daß sich die Öffnung bzw. der Flachtrichter 23 des Filmlegers 21 in einem geringen Abstand zur Oberfla¬ che der Formschale 1 befindet, wie dies in Fig. 8 gezeigt ist. Dadurch wird erreicht, daß der austretende Kraft¬ stoffström 20 sofort nach Verlassen des Filmlegers 21 ohne Zerstäubung auf die Oberflache/Kontur der Formschale 1 umgelenkt wird. Dadurch kann eine gewünschte Kraft¬ stoffverteilung auf der Formschale 1 eingestellt werden. Fig. 10 zeigt die Ansicht Z aus Fig. 8 auf den Kraft¬ stoff-Filmleger 21. Man erkennt den Kraftstoffkanal 22 sowie den Flachtrichter 23. Sinnvollerweise ist die Au- ßenkontur des Filmlegers 21 wie ersichtlich aerodynamisch geformt.For the function of the fuel film layer 21, it is important that it lies, as shown in FIG. 9, in the symmetry axis of the molded shell 1. Furthermore, it is important that the opening or the flat funnel 23 of the film layer 21 is at a short distance from the surface of the molded shell 1, as shown in FIG. 8. It is thereby achieved that the exiting fuel flow 20 is deflected onto the surface / contour of the molded shell 1 immediately after leaving the film layer 21 without atomization. A desired fuel distribution on the molded shell 1 can thereby be set. 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. As is evident, the outer contour of the film layer 21 is aerodynamically shaped.
Anstelle eines Kraftstoff-Filmlegers können auch eine oder mehrere Kraftstoff-Druckzerstauberdusen mit beliebi- ger Spritzdusencharakteristik in Verbindung mit einer er- findungsgemaßen Formschale 1 (Stromungsleitkorper) ange- ordnet sein, um eine gunstige Luft-Kraftstoff-Vermischung zu erzielen. Dabei wird auch von einer Druckzerstauber- düse in Analogie zum Filmleger Kraftstoff auf die konvexe Seite der Formschale 1 aufgebracht.Instead of a fuel film layer, 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. In this case, fuel is also applied to the convex side of the molded shell 1 by a pressure atomizing nozzle in analogy to the film layer.
Weitere Ausführungsbeispiele für einen aus zwei Formscha¬ len 1 bestehenden Doppelschalen-Zerstäuber mit einem Kraftstoff-Filmleger 21 - alternativ können Druckzer- stäuberdusen vorgesehen sein - zeigen die Fig. 11, 13, von denen in den Fig. 12, 14 jeweils Schnitte dargestellt sind. Dabei zeigt Fig. 11 einen doppelseitig beaufschlag¬ ten Doppelschalen-Zerstäuber mit zwei Formschalen, ahn¬ lich Fig. 5. In einem geeigneten Filmleger 21 wird der Kraftstoff auf zwei Kanäle 22 (hier ohne Flachtrichter 23) aufgeteilt. Es ist aber auch möglich, den Doppelscha¬ len-Zerstäuber nur einseitig zu beaufschlagen, wie dies die Fig. 12, 14 zeigen.11, 13, of which sections are shown in 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. In a suitable film layer 21, the fuel is divided into two channels 22 (here without a flat funnel 23). However, it is also possible to apply the double-shell atomizer only on one side, as shown in FIGS. 12, 14.
Der erfindungsgemaße Stromungsleitkorper 1 bzw. die er- findungsgemaße Formschale 1 wirken bei den zuletzt erläu¬ terten Ausfuhrungsbeispielen somit in Verbindung mit ei¬ nem Kraftstoff-Filmleger 21 als Schalenluftzerstäuber, wobei der Kraftstoff durch einen oder auch mehrere Kraft¬ stoffkanäle 22 zugeführt werden kann, wobei die Kraft- stoffkanäle 22 sowie ggf. in einem oder mehreren Flachtrichtern 23 munden und der Zerstäuber bzw. die Formschale 1 in geringem Abstand vom Flachtrichter 23 oder von der Mundung der Kanäle 22 angeordnet ist, und wobei der Filmleger 21 in der Symmetrieebene der For - schale(n) 1 liegt. Daneben kann ein erfindungsgemaßer Stromungsleitkorper bzw. eine Formschale 1 auch als Wir¬ belgenerator eingesetzt werden, der dann insbesondere aus einer oder auch mehreren beliebig geformten Formschalen 1 sowie einer oder auch mehreren dazu passenden Hutzen 15 besteht. Verwendet werden kann diese Anordnung zur Zumi- schung und Verdrallung kalter Luft bei Gasturbinen-Brenn- kammern. Dabei kann diese Anordnung an beliebiger Stelle auf dem Flammrohr beliebiger Brennkammern in beliebiger Lage angebracht werden. Generell kann bzw. können diese kegelförmige(n) Formschale(n) 1 der in Fig. 1 gezeigten Gestalt von beliebigem Querschnitt sein, wobei die von der Spitze 4 zur Basis bzw. Grundfläche 2 des Kegelaus¬ schnitts gehenden Strahlen keine Geraden sein müssen. Wie ausführlich erläutert, kann diese Formschale 1 als Luft¬ zerstäuber für beliebige flüssige Kraftstoffe verwendet werden. Es ist aber auch die Verwendung als Mischelement und Flammhalter bei Verwendung gasförmiger oder pulveri¬ sierter oder granulierter fester Kraftstoffe beliebiger Art möglich. Ferner können natürlich auch beliebige ver¬ schiedene Gas- oder Fluidströme miteinander vermischt werden. Dabei können eine Vielzahl von Details insbeson¬ dere konstruktiver Art durchaus abweichend von den ge¬ zeigten Ausführungsbeispielen gestaltet sein, ohne den Inhalt der Patentansprüche zu verlassen. 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. In addition, 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. In general, 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. As explained in detail, this molded shell 1 can be used as an air atomizer for any liquid fuel. However, it can also be used as a mixing element and flame holder when using gaseous or pulverized or granulated solid fuels of any kind. Furthermore, of course, 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.

Claims

Patentansprüche claims
1. Stromungsleitkorper für eine Gasturbinen-Brennkam- mer, auf den ein Fluidstrom (6) auftrifft, der hier¬ durch eine Veränderung seines Stromlinienfeldes er¬ fährt, gekennzeichnet durch eine spitz zulaufende Form¬ schale (1) von im wesentlichen kegelförmiger Ge- stalt, deren Grundflächen-Projektion (2) durch zu¬ mindest eine Gerade (3a) sowie eine die Endpunkte der Geraden (3a) verbindende beliebige Kurve (3b) gebildet ist, wobei die Formschale (1) im wesentli¬ chen mit ihrer Spitze (4) dem auf der Außenseite auftreffenden Fluidstrom (6) zugewandt ist.1. Flow guiding body for a gas turbine combustion chamber, which is hit by a fluid stream (6) which experiences a change in its streamline field, characterized by a tapered shaped shell (1) of essentially conical shape whose base surface projection (2) is formed by at least one straight line (3a) and any curve (3b) connecting the end points of the straight line (3a), the shaped shell (1) essentially having its tip (4th ) faces the fluid stream (6) hitting the outside.
2. Stromungsleitkorper nach Anspruch 1, dadurch gekennzeichnet, daß die Kurve (3b) keine signifikanten Eckpunkte besitzt.2. Stromungsleitkorper according to claim 1, characterized in that the curve (3b) has no significant corner points.
3. Stromungsleitkorper nach Anspruch 1 oder 2, dadurch gekennzeichnet, daß die durch die Spitze (4) sowie die Gerade (3a) definierte Ebene (5) der Form¬ schale (1) gegenüber der Anstromrichtung des Fluid- Stromes (6) geneigt ist (Anstellwinkel ß) . 3. Stromungsleitkorper according to claim 1 or 2, characterized in that the defined by the tip (4) and the straight line (3a) plane (5) of the Form¬ shell (1) with respect to the upstream direction of the fluid stream (6) is inclined (Angle of attack ß).
4. Stromungsleitkorper nach einem der vorangegangenen4. Stromungsleitkorper according to one of the preceding
Ansprüche, dadurch gekennzeichnet, daß mehrere Formschalen (1) einander benachbart, dabei jedoch zumindest be- reichsweise voneinander beabstandet, angeordnet sind.Claims, characterized in that a plurality of molded shells (1) are arranged adjacent to one another, but at least in some areas at a distance from one another.
5. Stromungsleitkorper nach einem der vorangegangenen Ansprüche, dadurch gekennzeichnet, daß die Formschale(n) (1) im Stromungsweg eines Luftstromes (6) und/oder eines Kraftstoffstromes (20) angeordnet ist/sind.5. Stromungsleitkorper according to one of the preceding claims, characterized in that the molded shell (s) (1) in the flow path of an air stream (6) and / or a fuel stream (20) is / are.
6. Stromungsleitkorper nach einem der vorangegangenen Ansprüche, dadurch gekennzeichnet, daß die Formschale (1) von einer Hutze (15) umgeben ist.6. Stromungsleitkorper according to one of the preceding claims, characterized in that the molded shell (1) is surrounded by a scoop (15).
7. Gasturbine mit zumindest einem Stromungsleitkorper nach einem der vorangegangenen Ansprüche, dadurch gekennzeichnet, daß der Stromungsleitkorper als Luftzerstauber oder als Flammhalter oder als Mi¬ scher oder als Wirbelgenerator fungiert.7. Gas turbine with at least one Stromungsleitkorper according to one of the preceding claims, characterized in that the Stromungsleitkorper acts as an air atomizer or as a flame holder or as a mixer or as a vortex generator.
8. Gasturbine mit zumindest einem Stromungsleitkorper nach einem der vorangegangenen Ansprüche, dadurch gekennzeichnet, daß der Stromungsleitkorper zur Zumischung und Verdrallung kalter Luft bei einer Brennkammer vorgesehen ist.8. Gas turbine with at least one flow guide body according to one of the preceding claims, characterized in that the flow guide body is provided for admixing and swirling cold air in a combustion chamber.
9. Gasturbine mit zumindest einem Stromungsleitkorper nach einem der vorangegangenen Ansprüche, dadurch gekennzeichnet, daß der Stromungsleitkorper mit einem Kraftstoff-Filmleger (21) oder einer Kraftstoff-Druckzerstauberduse kombiniert ist. 9. Gas turbine with at least one Stromungsleitkorper according to one of the preceding claims, characterized in that the Stromungsleitkorper is combined with a fuel film layer (21) or a fuel pressure atomizer nozzle.
EP95907643A 1995-02-03 1995-02-03 Flow-guiding body for gas turbine combustion chambers Expired - Lifetime EP0807213B1 (en)

Applications Claiming Priority (1)

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PCT/EP1995/000401 WO1996023981A1 (en) 1995-02-03 1995-02-03 Flow-guiding body for gas turbine combustion chambers

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EP0807213A1 true EP0807213A1 (en) 1997-11-19
EP0807213B1 EP0807213B1 (en) 2002-07-31

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US (1) US5918465A (en)
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CA (1) CA2209672C (en)
DE (1) DE59510303D1 (en)
WO (1) WO1996023981A1 (en)

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Also Published As

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US5918465A (en) 1999-07-06
CA2209672A1 (en) 1996-08-08
CA2209672C (en) 2006-06-06
WO1996023981A1 (en) 1996-08-08
DE59510303D1 (en) 2002-09-05
EP0807213B1 (en) 2002-07-31

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