EP3699493B1 - Système de chambre de combustion et dispositif de micro-turbine à gaz - Google Patents

Système de chambre de combustion et dispositif de micro-turbine à gaz Download PDF

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Publication number
EP3699493B1
EP3699493B1 EP20160469.1A EP20160469A EP3699493B1 EP 3699493 B1 EP3699493 B1 EP 3699493B1 EP 20160469 A EP20160469 A EP 20160469A EP 3699493 B1 EP3699493 B1 EP 3699493B1
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EP
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Prior art keywords
combustion chamber
chamber system
modular unit
subportion
wall
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EP20160469.1A
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German (de)
English (en)
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EP3699493A1 (fr
Inventor
Hannah Seliger-Ost
Matthias Lang
Andreas Huber
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Deutsches Zentrum fuer Luft und Raumfahrt eV
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Deutsches Zentrum fuer Luft und Raumfahrt eV
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/002—Wall structures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/02—Premix gas burners, i.e. in which gaseous fuel is mixed with combustion air upstream of the combustion zone
    • F23D14/04—Premix gas burners, i.e. in which gaseous fuel is mixed with combustion air upstream of the combustion zone induction type, e.g. Bunsen burner
    • F23D14/08—Premix gas burners, i.e. in which gaseous fuel is mixed with combustion air upstream of the combustion zone induction type, e.g. Bunsen burner with axial outlets at the burner head
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/46—Combustion chambers comprising an annular arrangement of several essentially tubular flame tubes within a common annular casing or within individual casings
    • 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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/60—Support structures; Attaching or mounting means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2206/00—Burners for specific applications
    • F23D2206/10—Turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00001—Arrangements using bellows, e.g. to adjust volumes or reduce thermal stresses
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00005—Preventing fatigue failures or reducing mechanical stress in gas turbine components

Definitions

  • the invention relates to a combustion chamber system, in particular for use in a gas turbine system, with a circumferential wall running around a longitudinal axis which delimits a combustion chamber in which a reaction zone is formed during operation, with a burner head arranged on the inlet side of the combustion chamber for adding fuel and oxidizer to the Combustion chamber, which comprises at least one fuel supply for adding fuel to the oxidizer, and with a combustion chamber outlet arranged on the outlet side of the combustion chamber.
  • the invention also relates to a micro gas turbine arrangement with a combustion chamber system.
  • combustion chamber systems are used, for example, in gas turbine systems and are, for example, from the EP 1 497 589 B1 and the EP 1 995 515 A1 known.
  • development of such combustion chamber systems aims to optimize pollutant emissions and ensure stable operation.
  • micro gas turbine systems in a power class of less than 1 MW
  • a wide operating range, at full and partial load should be covered due to the corresponding areas of application, e.g. in the field of combined heat and power.
  • a high degree of flexibility for example with regard to operation with different fuels, is sought.
  • a special known concept uses a combustion process management in which a pronounced, in particular inner, recirculation zone is formed in the combustion chamber, based on the so-called FLOX® principle ("Flameless Oxidation").
  • FLOX® principle “Flameless Oxidation”
  • Current combustion chamber systems based on the FLOX® principle are, for example, in " Zanger, J., Monz, T, Aigner, M., Experimental Investigation of the Combustion Characteristics of a double-staged FLOX®-based Combustor on an Atmospheric and a Micro Gas Turbine Test Rig, Proceedings of ASME Turbo Expo 15.-19 .
  • the installation position or location of the combustion chamber system in a turbine housing can have an influence, in particular if the outer boundary of the combustion chamber system is integrated into the geometry of gas ducts.
  • This can e.g. B. be cooling air ducts around the combustion chamber system.
  • the positioning or position of the combustion chamber system changes with respect to the housing, for example due to thermal expansion during operation, this can influence the geometry and change the supply of the combustion chamber system with fuel gas (oxidizer and / or fuel). This in turn can have a negative effect on the combustion process, in particular the stability and / or exhaust gas emissions.
  • DE 10 2015 226 079 A1 shows a combustion chamber device with a two-part flame tube.
  • the first flame tube part and the second flame tube part are displaceable relative to one another.
  • the two flame tube parts overlap one another in an overlapping section.
  • Another combustion chamber device is in the GB 1 420 202 A shown.
  • the invention is based on the object of providing a combustion chamber system which is positioned in a technical application in a largely defined manner during operation.
  • the invention is also based on the object of providing a micro gas turbine arrangement with such a combustion chamber system.
  • combustion chamber system is divided into at least a first and a second structural unit, which are arranged axially one behind the other in an installed state in a technical application, wherein the second structural unit extends at least partially downstream of the first structural unit, and that the structural units are axially relative are mounted displaceably to each other.
  • micro gas turbine arrangement For the micro gas turbine arrangement, the object is achieved with the features of claim 14.
  • This relates to a micro gas turbine arrangement with a combustion chamber system according to the invention, with a turbine connected downstream of the combustion chamber system and with a housing that surrounds at least the combustion chamber system by means of a wall, with at least one duct for gas ducting, in particular for air ducting, being formed between an area of the wall and the combustion chamber system is.
  • the design according to the invention achieves a division of the combustion chamber system, which can in particular be carried out perpendicular to the axial direction.
  • the second unit includes z. B. downstream of the first structural unit. In the transition, the structural units overlap at least in some areas.
  • the axial displaceability is such that at least the downstream end of the first Structural unit, in particular the first section of the peripheral wall, relative to the second structural unit, in particular the second partial section of the peripheral wall, are axially displaceable.
  • This design has the effect that changes in the axial position of one, e.g. The change in position or length is not transferred to the subsequent structural unit, since the axial movements of the structural units are decoupled from one another. Variations in position, in particular in length, of the combustion chamber system can thus be minimized.
  • This is particularly advantageous when the combustion chamber system is integrated into an internal geometry of a technical application, with precise positioning being required. This can be the case, for example, when the combustion chamber system forms a partial delimitation of a channel for conducting gas and changes in length of the combustion chamber system would influence the flow cross-section of the channel, which in turn can affect the combustion process.
  • the defined positioning thus contributes to a controlled, clean and stable combustion during operation.
  • Simple adaptation possibilities of the combustion chamber system result if the structural units are detachably (axially) arranged one behind the other in the installed state.
  • the structural units can then be present separately from one another during or after the dismantling of the combustion chamber system.
  • structural units that should be designed differently for a different mode of operation can be exchanged individually without the entire combustion chamber system having to be exchanged.
  • This can relate, for example, to elements that have an influence on a division of the oxidizer flow, such as, for example, mixed air openings in a section of the circumferential wall.
  • the first structural unit comprises a first section of the circumferential wall and the second structural unit comprises a second section of the circumferential wall.
  • the division of the combustion chamber system into the structural units is arranged adjacent to one or between two subsections.
  • the sections run z. B. each circumferentially around the longitudinal axis, so that there are pipe sections arranged axially one behind the other.
  • the division can be made, for example, perpendicular to the axial direction (i.e. to the longitudinal axis).
  • the modules arranged one behind the other overlap with one another in an axial overlap area, wherein in particular the first partial section overlaps with the second structural unit, in particular with the second partial section.
  • the inner circumference of the one, outer structural unit or the subsection is larger than the outer circumference of the other, inner structural unit or the subsection and is pushed over the inner structural unit or the inner subsection in the overlapping area.
  • the exact length of the overlap area can change depending on the axial displacement of the two subsections with respect to one another.
  • a tubular configuration of the circumferential wall is in the overlap area z.
  • B. a tube-in-tube arrangement In this way, a defined, easy-to-manufacture transition between two structural units or sub-sections can be obtained in a simple manner.
  • a stable mounting that is independent of the first structural unit for precise fixing of the second structural unit is achieved in that the second structural unit has at least one bearing means on its outer circumference which is designed to attach the second structural unit to a housing surrounding the combustion chamber system (e.g. the transition between two housing parts, such as a pressure housing and a turbine housing part).
  • a housing surrounding the combustion chamber system e.g. the transition between two housing parts, such as a pressure housing and a turbine housing part.
  • a reduction in the temperature load on the bearing means is achieved in that the bearing means is arranged in the overlap area, in particular between the first section and the second section. In this area z. B. due to a contact-free arrangement of the two structural units to each other and any air leakage into the combustion chamber, lower temperatures on the outside of the peripheral wall.
  • the storage means can thus be designed to be less temperature-resistant, which is usually associated with lower production costs and / or outlay.
  • the structural units, in particular the subsections are arranged in the overlapping area at least partially without contact with one another.
  • Touching elements may be present, e.g. B. spacer means to keep the gap.
  • Such a design enables simple, low-friction assembly and mobility of the subsections with respect to one another. Stress states in the material during axial movement to one another are reduced or avoided.
  • the gap is as small as possible in order to keep leakages between the combustion chamber and the outside area low, but preferably sufficiently large to be able to operate during operation, e.g. B. under thermal expansion to grant unimpaired mobility.
  • the combustion chamber system preferably comprises at least one anti-rotation device, by means of which the structural units arranged one behind the other (in particular with successive subsections) are mounted so as to be non-rotatable relative to one another in the circumferential direction.
  • This enables the structural units or the subsections to be precisely positioned relative to one another in the circumferential direction.
  • elements of the combustion chamber system that are assigned to different subsections or structural units can be arranged in a defined manner relative to one another in the circumferential direction.
  • One example are mixed air openings that are positioned in a defined position relative to feed nozzles of the burner head. This training contributes to an optimized, controlled combustion process.
  • the anti-rotation device is formed in the overlap area, one of the two structural units being arranged on the outside and one on the inside.
  • the anti-rotation device comprises an anti-rotation device, which is formed in particular on the inside of the outer structural unit in the overlap area, in particular the outer subsection, and also a receptacle, which is formed in particular on a downstream end of the inner structural unit, in particular the inner subsection.
  • the anti-rotation device can be guided axially in the receptacle.
  • the anti-rotation means is in particular as a projection, for. B. in the form of a "nose", a pin or a web.
  • the recess preferably extends axially longitudinally starting from the downstream end in the inner structural unit, for. B. as a slot in the inner section.
  • the receptacle is dimensioned in such a way that the anti-rotation device can protrude into it.
  • the anti-rotation device allows an axial relative movement, but prevents rotation.
  • the first structural unit comprises the burner head and the first section of the circumferential wall, which is in particular fastened to the burner head. With the first section, the first structural unit extends axially over the region of the reaction zone.
  • the second structural unit comprises the combustion chamber outlet. In and immediately downstream of the reaction zone, high temperatures arise during operation, which cause a relatively large thermal expansion of the first section. The change in length of the first section caused by this can be compensated for by movement relative to the second section due to the axial displaceability and therefore does not lead to a change in length of the entire combustion chamber system. This enables a largely defined position or positioning of the combustion chamber system over the entire length even during operation.
  • the first subsection preferably extends as far as possible in the direction of the combustion chamber outlet, so that the largest possible part of the change in length can be compensated for by thermal expansion of the combustion chamber system.
  • the first section can so, for. B. extend to an axial position at which the temperature of the exhaust gas z. B. is significantly reduced by adding secondary air, which also reduces thermal expansion.
  • the length of the first subsection or the division can expediently be selected such that elements or configurations of the combustion chamber system downstream of the reaction zone, which have to be adapted in different modes of operation (e.g. mixed air openings), are assigned to the second structural unit.
  • a second section of the circumferential wall can also be dispensed with and the first section is located in an area provided for this purpose in the second structural unit, e.g. B. at the combustion chamber outlet, expand.
  • the bearing means is preferably designed for arrangement in a gas guide section, in particular in a channel, wherein gas can pass through it.
  • the gas guide section is formed between the combustion chamber system and the surrounding housing of a technical application.
  • Passable by gas means that the bearing means is aerodynamically designed with a low locking effect, wherein it is z. B. blocked less than half of the flow cross-section. It can thus advantageously act at the same time as a (radial) spacer, which ensures a defined cross-sectional area of the channel and thus enables a uniform gas flow.
  • a ring-like element is particularly useful because it has a high level of stability and is relatively simple, e.g. B. as a turned and / or milled part is to be manufactured.
  • Such an advantageous gas-passable, stable design of the bearing means results, for. B., if the bearing means (in particular ring-shaped) is designed circumferentially, with a circumferential outer contact section for contact with a housing surrounding the combustion chamber system and with a circumferential inner contact section, which is arranged on the second structural unit, in particular on the second subsection, e.g. B. is attached, and when the two contact sections are connected to one another gas passable via radially arranged webs.
  • the outer contact section can have a circumferential, radially outwardly directed protrusion for easy axial fixation on the housing, the z. B. can engage in a groove of a flange connection.
  • a part-optimized and flow-optimized mounting of the first structural unit results when the first structural unit is mounted via the burner head (or at least parts thereof) and via a fuel supply line.
  • the fuel supply line can be dimensioned relatively large relative to the first structural unit and thus has good stability for its stable mounting.
  • the combustion chamber system is designed in such a way that, during operation, a secondary flow of oxidizer is branched off from a total oxidizer flow and is directed via the burner head into a channel between the circumferential wall and a wall surrounding the combustion chamber system.
  • the wall is assigned in particular to a housing surrounding the combustion chamber system.
  • the secondary current is z. B. used for cooling purposes, both convective by flowing past the peripheral wall and for cooling the exhaust gas by admixture behind the reaction zone through mixed air openings.
  • the ratio between the total oxidizer flow and the secondary flow is usually based on the geometry and a specific pressure loss ratio associated with it.
  • Changes in the length of the combustion chamber system can influence this ratio via changes in the geometry of the duct, which in turn can influence the combustion process. This can be reduced or avoided by the design of the combustion chamber system according to the invention. Simultaneously the ratio can be changed in a targeted manner by changing the geometry of the air supply of the duct and / or of existing mixed air openings due to the simple interchangeability of the second structural unit.
  • An advantageous embodiment results when mixed air openings are arranged in the second section of the circumferential wall, in particular circumferentially, through which, during operation, oxidizer of the secondary flow flows into the combustion chamber downstream of the reaction zone.
  • the admixture of oxidizer cools the exhaust gas before it enters the turbine, which significantly reduces the thermal load on the turbine and can also reduce the thermal expansion of the circumferential wall from the position of the mixed air openings.
  • the mixed air openings are assigned to the second section, the mixed air openings can be changed in a simple manner by simply replacing the second structural unit, e.g. B. if another mode of operation requires a different ratio of total to secondary current.
  • a particularly advantageous combustion chamber system is obtained when the combustion chamber system is designed for operation with a pronounced inner recirculation zone, in particular feed nozzles for supplying oxidizer and / or fuel via the burner head being arranged in a ring around the end wall of the burner head.
  • the feed nozzles are preferably located radially in the outer region, closer to the circumferential wall than to the longitudinal axis, preferably in the outer third.
  • the peripheral wall is for a symmetrical combustion z.
  • Combustion chamber systems of this type are for example in the not previously published German patent application No. 10 2016 118 632.5, filed with the DPMA on September 30, 2016 , and in the not pre-published German patent application No. 10 2016 118 633.3, filed with the DPMA on September 30, 2016 specified.
  • a flow-favorable design of the burner head and thus of the combustion chamber system is achieved if the end wall is at least partially designed to taper against the direction of flow of the oxidizer.
  • the end wall tapers conically, for example, and converges in particular symmetrically on the longitudinal axis. This reduces the flow loss through the oxidizer, which is directed via a plenum in the direction of the combustion chamber or around the combustion chamber. This contributes to optimizing the flow of the combustion chamber system and thus to increasing the overall efficiency of a system in which the combustion chamber system is used.
  • the branching off of a secondary flow from the oxidizer and its distribution to a channel around the circumferential wall can also take place in a flow-efficient manner.
  • the end wall is preferably designed as a wall instead of solid material.
  • Supply nozzles that are present in the combustion chamber are attached to the end wall and protrude at least upstream into the plenum, preferably also downstream into the combustion chamber.
  • the material thickness of the end wall can be as small as possible, but in such a way that sufficient stability is ensured even under the thermal load that is typical for combustion chamber systems. It has been found that such an end wall, which is as thin as possible, contributes to the stability of the combustion process: the low mass results in low thermal inertia. In this way, steady states in the combustion chamber system with stable combustion operation are reached more quickly.
  • a compact first structural unit with a stable mounting can be obtained in that the end wall merges upstream into a positioning element which is arranged on the longitudinal axis, and that the positioning element merges upstream into a distributor area and above it into a fuel supply line.
  • This is also a symmetrical, part-optimized and flow-efficient design of the combustion chamber system achievable.
  • the symmetry favors an optimized combustion process with low pollutant emissions.
  • Fig. 1 shows a sectional view of a combustion chamber system 1 with a burner head 4 and a combustion chamber 10.
  • the combustion chamber system 1 is designed for combustion process control according to the so-called "FLOX®" principle, in which a pronounced inner recirculation zone 22 is formed during operation.
  • FLOX® so-called "FLOX®” principle
  • the combustion chamber 10 comprises a combustion chamber 2 which is delimited by a peripheral wall 3 of the combustion chamber 10.
  • the circumferential wall 3 is arranged cylindrically about a longitudinal axis L, along which the combustion chamber system 1 extends axially.
  • mixed air openings 30 for supplying mixed air are introduced into the burned exhaust gas flowing out of the combustion chamber 10.
  • these are in a row in a ring-like manner, evenly distributed radially around the circumferential wall 3 and individually designed as circular bores, other opening shapes and also other arrangements being possible.
  • the burner head 4 is arranged on the inlet side of the combustion chamber 2 and has several, here by way of example six, feed nozzles 47 into the combustion chamber 2 for the addition of fresh gases to be burned (ie oxidizer, here further referred to as "(combustion) air", and fuel) opening feed openings 46.
  • the feed openings 46 are arranged uniformly circumferentially on an imaginary ring in an inlet-side end wall 40.
  • the ring, in particular a circular ring, on which the supply openings 46 are arranged, is located in the outer region of the end wall 40, so that the radial distance between the supply openings 46 (with respect to their midpoints) and the peripheral wall 3 is less than that of the longitudinal axis L.
  • the fresh gas " Air” can also be formed by another oxidizer and / or contain gas additives, such as exhaust gas, or thermally utilizable hydrocarbon compounds.
  • the fuel gas is z. B. natural gas is used, or another, in particular gaseous, fuel.
  • the burner head 4 comprises a fuel feed for adding fuel to the combustion air.
  • the end wall 40 is conically tapered against the direction of flow with respect to the combustion air in order to reduce the flow loss during operation compared to a flat design.
  • the fuel supply comprises a plurality of fuel nozzles 44, each of which here is one of the supply nozzles 47 to form air / fuel nozzle arrangements 41 are assigned.
  • a feed nozzle 47 protrudes with an upstream end formed here by a cylinder section into a plenum 49 and thus forms an air supply 45. here over a conical axial area, and protrudes with a tapered, downstream section through the end wall 40 into the combustion chamber 10.
  • the section protruding into the combustion chamber 10 is also cylindrical, but can also have a different shape.
  • the supply nozzles 47 extend along central longitudinal axes M, which are aligned parallel to the longitudinal axis L, for the axial supply of the partially premixed fuel-air mixture into the combustion chamber 10.
  • a non-premixed or technically completely premixed addition of the fresh gases is also possible, with the Burner head 4 is designed accordingly.
  • a branch line 43 of a finger-like line arrangement protrudes into each feed nozzle 47.
  • the branch lines 43 branch off like fingers from a central fuel supply line 42, whereby they have a certain line length, for example more than three times as long as the outer line diameter.
  • the branch lines 43 are designed with a change of direction, here bent for a favorable flow guidance, the angle ⁇ of the bends being greater than 90 ° and less than 180 ° .
  • one branch line 43 opens into a fuel nozzle 44 which is positioned directly upstream of the tapered section, with an opening immediately at the beginning of the acceleration section.
  • the fuel can thus be added coaxially to the inflowing combustion air, the combustion air being accelerated by the cross-sectional constriction immediately downstream of the fuel addition position.
  • a (partial) premixing of fuel and combustion air can take place up to the supply opening 46.
  • the fuel supply further comprises a central distributor area 421 arranged symmetrically on the longitudinal axis L and the branch lines 43 extending therefrom and opening into the fuel nozzles 44.
  • the branch lines 43 are fed with fuel via the distributor area 421 and a fuel supply line 42. This results in a symmetrical arrangement of the fuel supply in which a fuel plenum is not explicitly provided. This means that there is no need for a high pressure loss for even distribution of the fuel, as is usually the case with designs with a fuel plenum.
  • the burner head 4 and the peripheral wall 3 can have a radial positioning unit as an assembly aid (not shown here).
  • This can be formed, for example, by a nose-like projection in the outer area of the end wall 4 and a complementary receptacle in the peripheral wall 3.
  • the recording is z. B. designed and positioned so that the projection engages during the assembly of the burner head 4 and the peripheral wall 3.
  • the combustion chamber system 1 has a combustion chamber outlet 35, by means of which the combustion chamber system 1 merges into an exhaust line (not shown here) of an exhaust gas region 5.
  • the exhaust gas is fed to a turbine, for example, via the exhaust pipe.
  • the combustion chamber outlet 35 has a conical section 38, which is provided to reduce the cross-section from the circumferential wall 3 to the exhaust pipe in a streamlined manner.
  • the conical portion 38 can be fixed, e.g. B. be integrally connected to the peripheral wall 3.
  • the conical section 38 can also be dispensed with.
  • the combustion chamber system 1 is mounted in a housing of a technical application, the wall 8 of which in FIG Fig. 1 is partially indicated schematically.
  • this can be the housing of a micro gas turbine arrangement, for example with a pressure housing part 81, which houses a large part of the combustion chamber system 1, and with a turbine housing part 82, which are connected via a flange connection 83 (indicated here).
  • a duct 84 for guiding air is formed between the wall 8 and the outside of the peripheral wall 3.
  • the channel 84 is used to guide the secondary air which, during operation, is divided from the total air flow of the plenum 49 upstream of the end wall 40.
  • the wall 8 converges in the area of the conical section 38 in a, here conical, cross-sectional constriction.
  • the flow cross-section of the channel 84 in the area of the cross-sectional constriction depends, among other things, on the axial length of the combustion chamber system 1.
  • the combustion chamber system 1 is axially divided into two structural units 36 and 37, which are mounted so as to be axially displaceable relative to one another.
  • the storage takes place separately from one another.
  • More than two structural units 36, 37 which form the combustion chamber system 1 are also possible.
  • the structural units 36 and 37 are each assigned an axial section 30, 31 of the circumferential wall 3, so that the circumferential wall 3 is divided into two axial subsections 30, 31.
  • the structural units 36, 37 with the subsections 30, 31 are arranged axially one behind the other and in their transition relative to one another so as to be axially displaceable.
  • At least one downstream end 39 of the first subsection 30 is axially displaceable with respect to the second subsection 31.
  • the first structural unit 36 which is arranged further upstream, furthermore comprises the burner head 4, on the end wall 40 of which the circumferential wall 3 is attached circumferentially and from which the first section 30 of the circumferential wall 3 extends.
  • the first section 30 has an axial length such that it extends at least over a reaction zone 21 in which the rapid combustion reactions take place during operation.
  • the second structural unit 37 includes the combustion chamber outlet 35 with the conical section 38.
  • the mixed air openings 34 are also provided in the second sub-section 31 of the circumferential wall 3.
  • the two structural units 36, 37 are detachably mounted in such a way that the subsections 30, 31 are arranged directly axially one behind the other. “Detachable” means that the structural units 36, 37 can be separated or are present separately during or after dismantling.
  • a defined, axially gapless transition between the two subsections 30, 31 is achieved in that the two subsections 30, 31 overlap one another in an axial overlap region 32.
  • the inside diameter of the second subsection 31 is slightly larger than the outside diameter of the first subsection 30, so that the first subsection 30 can be pushed into the second subsection 31 during assembly.
  • the inner diameter of the second subsection 31 is selected to be larger in such a way that the two subsections 30, 31 are arranged in a contact-free manner with the formation of an annular gap 33 in the overlapping area 32 (apart from, for example, any anti-rotation means and / or guide means and / or Spacer means 381).
  • This allows simple assembly and good axial mobility with respect to one another.
  • the annular gap 33 is so wide radially that even with z. B. deformations during operation, the axial mobility to each other is maintained, but otherwise as close as possible in order to keep air leakage between the channel 84 and the combustion chamber 2 low.
  • the combustion chamber system 1 is integrated into a gas routing geometry (here the air routing geometry) of a gas turbine system, the change in length can change this geometry .
  • the combustion chamber outlet 35 with the conical section 38 is displaced axially in the direction of the turbine housing part 82, which reduces the flow cross section of the channel 84. This influences the pressure loss ratios in the gas flow and thus the ratio of the air distribution (combustion air to secondary air), which has a direct influence on the combustion process and thus the exhaust gas emissions.
  • the change in length of the combustion chamber system 1 caused by thermal expansion is largely compensated for by the axial relative movement of the subsections 30, 31 with respect to one another.
  • the first section 30 of the circumferential wall 3 pushes axially further under the second section 31 of the circumferential wall 3 to be able to compensate.
  • the overlap area 32 increases by the axial length extension, but the total length of the combustion chamber system 1 remains largely unchanged.
  • the total length varies essentially around the length expansion of the second structural unit 37. This length expansion falls due to the lower gas temperatures there (in particular also due to the admixture of mixed air) and the comparatively short length of the second structural unit 37 the end.
  • the flow cross section of the channel 84 thus remains essentially unchanged.
  • the pressure loss ratios in the flow guide and thus the ratio of the air distribution remain essentially constant. This contributes to a defined combustion process management.
  • the two structural units 36, 37 are expediently mounted separately from one another for an axially displaceable mounting of the subsections 30, 31.
  • the second structural unit 37 is mounted on the housing of the technical application surrounding it, here the micro gas turbine arrangement.
  • the second structural unit 37 in the present case has a bearing means 6 which is fastened to the outer circumference of the second partial section 31.
  • the bearing means 6 is mounted on the flange connection 83 between the two housing parts 81, 82, as a result of which the bearing means 6 can be easily mounted and the second structural unit 37 is securely mounted.
  • the bearing means 6 is designed in such a way that it can be arranged circumferentially in a gas guide section, here the channel 84, wherein the gas can pass through it.
  • the bearing means 6 is advantageously designed in such a way that it has a low flow resistance, but at the same time is sufficiently stable for secure storage.
  • the bearing means 6 has a ring structure.
  • the bearing means 6 comprises an annular outer contact section 61 for contact with the surrounding housing and an inner contact section 63 with which the bearing means 6 is attached to the second section 31 of the peripheral wall 3 and thus forms part of the second structural unit 37.
  • the contact sections 61, 63 are designed to be ring-like and preferably thin-walled for secure contact or good fastening options with a shape that is low in resistance at the same time.
  • the material thickness is at least sufficiently thick, in order to give the contact sections 61, 63 the stability required for storage.
  • the outer contact section 61 has a circumferential, radially outwardly directed projection 62 which is here axially centered. With the supernatant 62, the bearing means 6 engages z. B. into a groove formed in the flange connection 83. The bearing means 6 can be clamped between the flanges, whereby a defined positioning of the bearing means 6 and thus the second structural unit 37 is advantageously achieved. When the combustion chamber system 1 is mounted vertically, the bearing means 6 with the projection 62 could also rest on the flange of the turbine housing part 82 and be supported against it (not shown here).
  • the two contact sections 61, 63 are connected to one another in a stable manner by webs 64 extending radially (with respect to the longitudinal axis L), here six in number by way of example.
  • the bearing means 6 also acts as a radial spacer ring. This ensures a uniform radial distance between the combustion chamber system 1 and the wall 8, and thus a uniform, symmetrical flow cross section of the channel 84. This contributes to a symmetrical air flow.
  • one or more spacing means 381 can additionally be present on the second structural unit 37 in order to keep the flow cross-section of the channel 84 as constant as possible.
  • the spacing means 381 are arranged in the form of projections on the outside of the conical section 38 for contact with the wall 8. In particular, they serve to additionally fix the second structural unit 37 and to change the position of the second structural unit 37, for. B. counteract by deformations.
  • the bearing means 6 is fastened to the second structural unit 37 in the overlap region 32.
  • the overlap area 32 corresponds in its axial extent z. B. approximately the axial extent of the bearing means 6 or the inner contact section 63.
  • the overlap region 32 can also be longer, in particular in the Operation in which the overlap area 32 increases axially by the displacement due to thermal expansion.
  • the fastening of the bearing means 6 in the overlap region 32 has the advantage that the thermal load on the contact section 63 is reduced. This results in particular from the contact-free arrangement of the subsections 30, 31 with respect to one another, the annular gap and any air leakage into the combustion chamber 2 reducing the heat transfer between the combustion chamber 2 and the contact section 63.
  • the first structural unit 36 is supported in a part-optimized manner via the burner head 4, which is connected to the first section 30.
  • the bearing forces are transmitted via the end wall 40, which merges upstream into a rod-like positioning element 48 which is arranged centrally on the longitudinal axis L.
  • the positioning element 48 merges upstream into the distributor region 421 and above it into the fuel supply line 42.
  • the first structural unit 36 is fixed via the fuel supply line 42 upstream of the combustion chamber system 1 (not shown here).
  • the bearing is designed to be flow-efficient, thanks to the low-resistance shape of the end wall 4, which is conical in the direction of flow, and the central, compact cross-section arrangement and design of the positioning element 48, the distributor area 421 and the fuel supply line 42. This means that a flow-efficient, stable bearing is achieved at the same time.
  • the combustion chamber system 1 comprises an anti-rotation device 7, by means of which the two structural units 36, 37 and thus the subsections 30, 31 are mounted so as to be non-rotatable relative to one another in the circumferential direction.
  • a fixed positioning of the two structural units 36, 37 is achieved in the radial direction.
  • elements or formations in both structural units 36, 37 can be positioned in a defined manner in relation to one another in the circumferential direction.
  • this concerns z. B. the feed openings 46 of the burner head 4, which are arranged radially clearly defined to the mixed air openings 34 of the second assembly 37, z. B. so that two mixed air openings 34 each lie radially between two supply openings 46. This enables a defined, clean combustion process management.
  • the anti-rotation device 7 is formed in the overlap region 32.
  • the anti-rotation device 7 comprises an anti-rotation device 71, which in the present case is designed as a projection on the inside of the outer, here the second, partial section 31, e.g. B. in the form of a "nose", a web or pin.
  • the anti-rotation device 7 comprises a receptacle 72, which is formed here on the end 39 of the inner, first partial section 30.
  • the receptacle 72 is introduced into the end 39 of the first section 30 in the manner of an axially extending elongated recess, for example as a slot.
  • the recess is so wide that the anti-rotation means 71 can protrude, the anti-rotation means 71 having a corresponding radial height.
  • the axial length of the recess corresponds at least to the path of the expected axial displacement in which the thermal expansion results in this area.
  • the first sub-section 30 is thus movable or displaceable and radially guided with its end 39 relative to the second sub-section 31 over the entire path of thermal expansion.
  • Another advantage of the division of the combustion chamber system 1 described here is that the air conditions can be influenced with little effort. Should z. B. the combustion chamber system 1 can be used flexibly, for example with different fuels, this often requires an adjustment of the air conditions. As a result of the division of the combustion chamber system 1 described here, in particular the mixed air ratio can be adapted with little effort by exchanging the second structural unit 37.
  • Fig. 1 the air flow is indicated by arrows.
  • the air is divided according to a certain ratio into a secondary air flow and a combustion air flow.
  • the secondary air is conducted along the end wall 40 into the channel 84, the flow guidance being designed to be low in resistance due to the conical tapering of the end wall 40.
  • the secondary air flowing around the combustion chamber 10 cools the end wall 40 and the peripheral wall 3, in particular convectively.
  • the mixed air openings 34 part of the secondary air enters the combustion chamber 10 as mixed air.
  • the remainder flows further in the direction of the exhaust gas area 5.
  • the ratio of the division of total air (or combustion air) to secondary air and mixed air to remaining air in the secondary air is determined by the geometry of the Flow guidance, in particular the formation of the mixed air openings 34 and the channel 84, determined.
  • the remaining air enters the air / fuel nozzle assemblies 41 as combustion air through the air feeds 45.
  • the combustion air fuel is added coaxially to the main flow direction into the feed nozzles 47 immediately upstream of the cross-sectional constrictions, so that the combustion air with the added fuel is generated via the acceleration paths formed by the cross-sectional constrictions is accelerated.
  • a partial mixing of combustion air and fuel takes place up to the outlet openings 46. This mixture is now fed to the combustion chamber 10, where it ignites and is burned in the reaction zone 21.
  • a recirculation flow is formed with an internal recirculation of the burned exhaust gas, by means of which part of the burned exhaust gas is returned to an area upstream of the combustion zone and mixes with the still unburned fresh gases (in the figure through Arrows indicated). In this way the combustion temperature is reduced.
  • the feed openings 46 which are arranged relatively far outward, are beneficial an essentially inwardly directed recirculation so that the returning exhaust gases in the inner recirculation zone 21, surrounded by the annular combustion zone, flow back, ie closer to the longitudinal axis L than the burning gases.
  • the essentially internal recirculation achieves a compact flow guide, which in turn allows the combustion chamber 10 to be designed to be compact, in particular with regard to its length.
  • the burner head 4 and the combustion chamber 10 are designed in such a way that the reaction zone 21 and recirculation zone 22 are located upstream of the mixed air openings 34.
  • the mixed air added through the mixed air openings 34 essentially mixes with the exhaust gas flowing in the downstream direction into the exhaust gas region 5 and cools it.
  • the burner head 4 and the combustion chamber 10 are, for. B. designed such that there is a recirculation rate (mass ratio of recirculated exhaust gas to added fresh gases) of less than 1.5, preferably less than 1, for example 0.4 to 0.8. This recirculation rate allows stable, clean combustion over a wide operating range.
  • the specified combustion process management enables low-emission, stable and efficient operation of the micro gas turbine arrangement.
  • the design of the combustion chamber system 1 according to the invention contributes to the advantageous operation in that the ratios according to the design between the air flows can be adhered to more precisely.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)

Claims (14)

  1. Système de chambre de combustion (1), en particulier destiné à l'utilisation dans une installation de turbine à gaz
    comportant une paroi circonférentielle (3) s'etendant autour d'un axe longitudinal (L), laquelle délimite un espace de combustion (2) dans laquelle une zone de réaction (21) est formée pendant le fonctionnement,
    comportant une tête de combustion (4), disposée côté entrée de la chambre de combustion (2), pour ajouter du combustible et de l'oxydant dans l'espace de combustion (2), laquelle comprend au moins une alimentation en combustible destinée à l'ajout de combustible dans l'oxydant, et comportant une évacuation despace de combustion (35) disposée côté sortie de l'espace de combustion (2),
    dans lequel le système de chambre de combustion (1) est subdivisé en une première et/ou une seconde unité structurelle (36, 37), lequelles, à l'état installé dans une application technique, sont disposées de manière axiale l'une derrière l'autre, la seconde unité structurelle (37) s'étendant au moins par zones en aval de la première unité structurelle (36),
    dans lequel les unités structurelles (36, 37) sont montées de manière à pouvoir être déplacées de manière axiale l'une par rapport à l'autre,
    dans lequel la première unité structurelle (36) comprend une première section partielle (30) de la paroi circonférentielle (3), et
    dans lequel la seconde unité structurelle (37) comprend une seconde section partielle (31) de la paroi circonférentielle (3),
    dans lequel la division du système de chambre de combustion (1) en unités structurelles (36, 37) est disposée de manière adjacente sur une ou entre deux sections partielles (30, 31),
    dans lequel les unités structurelles (36, 37) disposées l'une derrière l'autre se chevauchent dans une zone de chevauchement (32) axiale, dans lequel la première section partielle (30) chevauche en particulier la seconde unité structurelle (37), en particulier la seconde section partielle (31), et
    dans lequel la seconde unité structurelle (37) comporte au moins un moyen de montage (6) sur sa circonférence externe, ledit moyen de montage étant conçu pour monter la seconde unité structurelle (37) sur un carter (81, 82) entourant le système de chambre de combustion (1) à l'état installé,
    caractérisé en ce
    que le moyen de montage (6) est disposé dans la zone de chevauchement (32).
  2. Système de chambre de combustion (1) selon la revendication 1,
    caractérisé en ce
    que les unités structurelles (36, 37) sont disposées dans la zone de chevauchement (32) au moins partiellement sans contact les unes avec les autres.
  3. Système de chambre de combustion (1) selon l'une quelconque des revendications précédentes,
    caractérisé en ce
    que le système de chambre de combustion (1) comprend au moins un dispositif anti-rotation (7), au moyen duquel les unités structurelles (36, 37) disposées l'une derrière l'autre sont montées dans le sens circonférentiel de manière à être bloquées en rotation.
  4. Système de chambre de combustion (1) selon la revendication 3,
    caractérisé en ce
    que le dispositif anti-rotation (7) est conçu dans la zone de chevauchement (32), dans lequel l'une des deux unités structurelles (36, 37) est disposée à l'extérieur et l'autre à l'intérieur, et le dispositif anti-rotation (7) comprend un moyen anti-rotation (71), lequel est formé en particulier sur la face interne de l'unité structurelle externe (37), en particulier de la section partielle (31) externe, et comprend en outre un logement (72), lequel est formé en particulier à une extrémité (39) aval de l'unité structurelle (36) interne, en particulier de la section partielle (30) interne, et
    que le moyen anti-rotation (71) est guidé de manière axiale dans le logement (72).
  5. Système de chambre de combustion (1) selon l'une quelconque des revendications précédentes, caractérisé en ce
    que la première unité structurelle (36) comprend la tête de combustion (4), ainsi que la première section partielle (30) et s'étend au-delà de la zone de la zone de réaction (21) de manière axiale avec la première section partielle (30) et/ou que la seconde unité structurelle (37) comprend l'évacuation d'espace de combustion (35).
  6. Système de chambre de combustion (1) selon l'une quelconque des revendications précédentes,
    caractérisé en ce
    que le moyen de montage (6) est conçu de manière à être disposé dans une section de guidage de gaz, en particulier dans un canal (8) et dans lequel il peut être traversé par le gaz.
  7. Système de chambre de combustion (1) selon la revendication 6,
    caractérisé en ce
    que le moyen de montage (6) est conçu de manière circonférentielle, et comporte une section d'appui (61) externe périphérique destinée à l'appui sur un carter entourant le système de chambre de combustion (1) et comporte une section d'appui (63) interne périphérique, laquelle est disposée au niveau de la deuxième unité structurelle (37), en particulier au niveau de la seconde section partielle (31), et
    que les deux sections d'appui (61, 63) sont reliées l'une à l'autre, au moyen des nervures (64) disposées de manière radiale, de manière à laisser passer les gaz.
  8. Système de chambre de combustion (1) selon les revendications 5 à 7,
    caractérisé en ce
    que la première unité structurelle (36) est montée par l'intermédiaire de la tête de combustion (4) et par l'intermédiaire d'une conduite d'alimentation en combustible (42).
  9. Système de chambre de combustion (1) selon l'une quelconque des revendications précédentes,
    caractérisé en ce
    que le système de chambre de combustion (1) est conçu de telle sorte que, pendant le fonctionnement, un flux secondaire d'oxydant est dévié d'un flux total d'oxydant et conduit, par l'intermédiaire de la tête de combustion (4), dans un canal (84) entre la paroi circonférentielle (3) et une paroi (8) entourant le système de chambre de combustion (1).
  10. Système de chambre de combustion (1) selon l'une quelconque des revendications précédentes,
    caractérisé en ce
    que dans la seconde section partielle (31) de la paroi circonférentielle (3), des ouvertures d'air mélangé (34) sont disposées, en particulier de manière périphérique, à travers lesquelles, pendant le fonctionnement, l'oxydant du flux secondaire s'écoule dans l'espace de combustion (2), en aval de la zone de réaction (21).
  11. Système de chambre de combustion (1) selon l'une quelconque des revendications précédentes,
    caractérisé en ce
    que le système de chambre de combustion (1) est conçu pour fonctionner avec une zone de recirculation (22) intérieure prononcée, dans lequel, en particulier des buses d'alimentation (47) destinée à l'alimentation en oxydant et/ou en combustible sont disposées en couronne autour d'une paroi frontale (40) de la tête de combustion (4).
  12. Système de chambre de combustion (1) selon la revendication 11,
    caractérisé en ce
    que la paroi frontale (40) est conçue de manière au moins partiellement conique à l'opposé du sens d'écoulement de l'oxydant
  13. Système de chambre de combustion (1) selon la revendication 11 ou 12,
    caractérisé en ce
    que la paroi frontale (40) se transforme en amont dans un élément de positionnement (48) disposé sur l'axe longitudinal (L), et
    que l'élément de positionnement (48) se transforme en amont dans une zone de distribution (421) et, au-dessus de celle-ci, dans une conduite d'alimentation en combustible (42).
  14. Agencement de micro-turbine à gaz comportant un système de chambre de combustion (1) selon l'une quelconque des revendications précédentes, comportant une turbine raccordée en aval du système de chambre de combustion (1) et comportant un carter, lequel entoure au moins le système de chambre de combustion (1) au moyen d'une paroi (8), dans lequel, entre une zone de la paroi (8) et le système de chambre de combustion (1), au moins un canal (84) destiné au guidage du gaz, en particulier au guidage de l'air, est formé.
EP20160469.1A 2018-02-28 2019-02-18 Système de chambre de combustion et dispositif de micro-turbine à gaz Active EP3699493B1 (fr)

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DE102018104543.3A DE102018104543A1 (de) 2018-02-28 2018-02-28 Brennkammersystem und Mikrogasturbinenanordnung
EP19157668.5A EP3534070B1 (fr) 2018-02-28 2019-02-18 Système de chambre de combustion et dispositif de micro-turbine à gaz

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EP19157668.5A Division-Into EP3534070B1 (fr) 2018-02-28 2019-02-18 Système de chambre de combustion et dispositif de micro-turbine à gaz

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GB2599424A (en) * 2020-10-01 2022-04-06 Bosch Thermotechnology Ltd Uk An air-gas mixture burning appliance with a gas flow distance regulating device

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Publication number Priority date Publication date Assignee Title
US2768497A (en) * 1951-02-03 1956-10-30 Gen Motors Corp Combustion chamber with swirler
GB1420202A (en) * 1972-03-16 1976-01-07 Stone Platt Crawley Ld Combustion chambers
DE3930569C2 (de) * 1989-09-13 1995-06-01 Siegfried W Schilling Brennerkopf
GB2299399A (en) * 1995-03-25 1996-10-02 Rolls Royce Plc Variable geometry air-fuel injector
DE10217913B4 (de) 2002-04-23 2004-10-07 WS Wärmeprozesstechnik GmbH Gasturbine mit Brennkammer zur flammenlosen Oxidation
EP1995515B1 (fr) 2007-05-23 2013-10-30 WS-Wärmeprozesstechnik GmbH Fonctionnement FLOX pris en charge et son brûleur
DE102012216080A1 (de) * 2012-08-17 2014-02-20 Dürr Systems GmbH Brenner
DE102015226079A1 (de) * 2015-12-18 2017-06-22 Dürr Systems Ag Brennkammervorrichtung und Gasturbinenvorrichtung
DE102016118632A1 (de) 2016-09-30 2018-04-05 Deutsches Zentrum für Luft- und Raumfahrt e.V. (DLR) Brennkammersystem, Verwendung eines Brennkammersystems mit einer angeschlossenen Turbine und Verfahren zur Durchführung eines Verbrennungsprozesses
DE102016118633B4 (de) 2016-09-30 2021-03-25 Deutsches Zentrum für Luft- und Raumfahrt e.V. Brennerkopf, Brennersystem und Verwendung des Brennersystems

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DE102018104543A1 (de) 2019-08-29
EP3534070B1 (fr) 2020-11-18
EP3534070A1 (fr) 2019-09-04

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