EP0727615A1 - Fuel injector for gas turbine combustion chamber - Google Patents

Abstract

The assembly consists of an injector (27) discharging into a pre-vaporisation chamber (21). At least two pre-vaporisation ducts (19) connect the chamber to inlet ports (20) of pre-mixing chambers (12) leading to the combustion chamber (6). The pre-vaporisation chamber (21) has inlets (30) for a pressurised pre-vaporisation fuel, and each of the mixing chambers has an inlet (18,24,32,34,36) for fuel under dilution pressure. The cross-section of the fuel pre-vaporisation inlets (30) and the pressure of the pre-vaporisation fuel are such that the pre-vaporised mixture has a richness greater than that of a stoichiometric mixture. The section of the dilution fuel inlets and the pressure of this fuel are such that the mixture contained in each pre-mixing chamber has a richness below that of the stoichiometric mixture. The pre-vaporisation ducts (19) are connected in parallel with the pre-vaporisation chamber, with a diaphragm (25) between them, and the injector has a protective cap (28) with apertures.

Description

FR-A-1 590 542 describes a fuel injection assembly intended to equip a gas turbine combustion chamber, comprising a fuel injector opening into a pre-vaporization chamber and at least two pre-vaporization conduits connected to said combustion chamber pre-vaporization which they connect to two intake orifices of the pre-evaporated mixture in premix chambers which are separate from each other and which are each separate from the pre-vaporization chamber and which open into the combustion chamber, the pre-vaporization chamber being provided with '' inlet ports for oxidizer under pre-vaporization pressure and each premix chamber being provided with an inlet device for oxidizer under dilution pressure.

The main problems, to date unsolved or poorly resolved, relating to known fuel injection systems reside, on the one hand, in an excessive production of nitrogen oxides (NO _X ) and fumes, on the other hand part, in the risk of self-ignition of the oxidizer / fuel mixture, and of poorly controlled combustion that results.

To remedy these drawbacks, the invention proposes the adoption of a set of provisions making it possible to obtain a pre-vaporization of the injected fuel free from the risk of self-ignition and to produce oxidizer / fuel premixes having riches lower than that of a stoichiometric mixture, further propelled at high speed, preferably with turbulence to ensure, in the combustion chamber, lean and complete combustion.

To do this, according to the invention, the cross section of the inlet orifice (s) of the pre-vaporization oxidant and the pressure of said pre-vaporization oxidant have values such that the pre-evaporated mixture has a higher richness than that of a stoichiometric mixture, however that the intake section of the dilution oxidizer intake device and the pressure of said dilution oxidant have values such that the mixture contained in each premix chamber has a lower richness than that of a stoichiometric mixture.

• lesdits conduits de prévaporisation sont raccordés en parallèle à la chambre de prévaporisation, avec interposition d'un diaphragme entre chaque conduit de prévaporisation et la chambre de prévaporisation;
• l'ensemble d'injection comprend un diaphragme unique interposé entre lesdits conduits de prévaporisation et la chambre de prévaporisation;
• l'aval étant la partie de la chambre de combustion la plus éloignée de l'injecteur de carburant, chaque orifice d'admission du mélange prévaporisé dans une chambre de prémélange est orienté vers l'aval;
• l'ensemble d'injection comporte une coiffe de protection de l'injecteur de carburant qui isole ledit injecteur de carburant du reste de la chambre de combustion;
• ladite coiffe de protection comporte une première ouverture raccordée à ou aux orifices d'admission du comburant de prévaporisation de la chambre de prévaporisation et une deuxième ouverture raccordée à une source de comburant sous pression;
• ladite première ouverture entoure la paroi de la chambre de prévaporisation en en étant écartée de manière à ménager un espace annulaire qui forme ladite deuxième ouverture;
• la paroi délimitant ladite coiffe de protection est munie d'orifices traversant qui débouchent dans les chambres de prémélange et qui constituent des premiers orifices d'admission de comburant de dilution des mélanges contenus dans lesdites chambres de prémélange;
• chaque dispositif de dilution comprend au moins une vrille hélicoïdale d'admission du comburant de dilution, qui est coaxiale à l'orifice d'admission du mélange prévaporisé;
• chaque chambre de prémélange comprend une paroi tubulaire, cependant que chaque dispositif de dilution comprend une vrille hélicoïdale unique et un ou plusieurs deuxièmes orifices d'admission de comburant de dilution, qui traversent ladite paroi et sont situés de manière sensiblement opposée à ou auxdits premiers orifices d'admission de comburant de dilution;
• chaque chambre de prémélange comprend une paroi tubulaire, chaque dispositif de dilution comprenant uniquement deux vrilles hélicoïdales;
• l'aval étant la partie de la chambre de combustion la plus éloignée de l'injecteur de carburant, chaque chambre de prémélange comporte une paroi tubulaire convergente vers l'aval et un orifice aval de communication avec la chambre de combustion;
• ladite paroi tubulaire est sensiblement tronconique;
• l'ensemble d'injection fait partie d'un système d'injection de carburant correspondant au fonctionnement "PLEIN GAZ" de la chambre de combustion.

The following advantageous arrangements are also preferably adopted:

• said pre-vaporization ducts are connected in parallel to the pre-vaporization chamber, with the interposition of a diaphragm between each pre-vaporization duct and the pre-vaporization chamber;
• the injection assembly comprises a single diaphragm interposed between said pre-vaporization conduits and the pre-vaporization chamber;
• the downstream being the part of the combustion chamber furthest from the fuel injector, each inlet orifice for the mixture evaporated in a premix chamber is oriented downstream;
• the injection assembly includes a protective cap for the fuel injector which isolates said fuel injector from the rest of the combustion chamber;
• said protective cap has a first opening connected to one or more of the inlet apertures of the evaporating oxidizer from the evaporating chamber and a second opening connected to a source of oxidizing agent under pressure;
• said first opening surrounds the wall of the pre-vaporization chamber, being spaced apart so as to provide an annular space which forms said second opening;
• the wall delimiting said protective cap is provided with through orifices which open into the premix chambers and which constitute first intake orifices for diluting oxidizer of the mixtures contained in said premix chambers;
• each dilution device comprises at least one helical spiral for admitting the dilution oxidant, which is coaxial with the inlet of the pre-evaporated mixture;
• each premix chamber includes a tubular wall, while each dilution device includes a single helical spin and one or more second dilution oxidant inlet ports, which pass through said wall and are located substantially opposite to said first port (s) admission of dilution oxidizer;
• each premix chamber includes a tubular wall, each dilution device comprising only two helical tendrils;
• the downstream being the part of the combustion chamber furthest from the fuel injector, each premix chamber has a tubular wall converging downstream and a downstream orifice for communication with the combustion chamber;
• said tubular wall is substantially frustoconical;
• the injection assembly is part of a fuel injection system corresponding to the "FULL GAS" operation of the combustion chamber.

The main advantage of the invention lies precisely in obtaining a satisfactory, low-pollution combustion, with a reduced production of nitrogen oxides and fumes, and the elimination of the risks of self-ignition and return of flames ("flash-back").

The invention will be better understood, and secondary characteristics and their advantages will become apparent during the description of embodiments given below by way of example.

It is understood that the description and the drawings are given for information only and are not limiting.

• la figure 1 est une coupe axiale simplifiée d'une chambre de combustion munie d'un ensemble d'injection de carburant conforme à l'invention;
• la figure 2 est une coupe axiale d'une première réalisation d'un ensemble d'injection de carburant conforme à l'invention;
• la figure 3 est une coupe suivant III-III de la figure 2;
• la figure 4 est une coupe axiale, analogue à celle de la figure 2, d'une deuxième réalisation d'un ensemble d'injection de carburant conforme à l'invention;
• la figure 5 est une coupe axiale schématique d'une chambre de combustion munie d'ensembles d'injection de carburant conformes à l'invention;
• la figure 6 est une vue suivant F6 de la figure 5;
• la figure 7 est une coupe axiale, analogue à celle de la figure 5, d'une autre chambre de combustion munie d'ensembles d'injection de carburant conformes à l'invention; et,
• la figure 8 est une vue suivant F8 de la figure 7.

Reference will be made to the accompanying drawings, in which:

• Figure 1 is a simplified axial section of a combustion chamber provided with a fuel injection assembly according to the invention;
• Figure 2 is an axial section of a first embodiment of a fuel injection assembly according to the invention;
• Figure 3 is a section along III-III of Figure 2;
• Figure 4 is an axial section, similar to that of Figure 2, of a second embodiment of a fuel injection assembly according to the invention;
• Figure 5 is a schematic axial section of a combustion chamber provided with fuel injection assemblies according to the invention;
• Figure 6 is a view along F6 of Figure 5;
• Figure 7 is an axial section, similar to that of Figure 5, of another combustion chamber provided with fuel injection assemblies according to the invention; and,
• FIG. 8 is a view along F8 of FIG. 7.

• un axe 1 de sensible symétrie;
• une virole externe 2 ayant l'axe 1 pour axe de révolution;
• une virole interne 3 ayant l'axe 1 pour axe de révolution;
• un fond transversal 4 reliant les deux viroles 2 et 3, disposé en amont par rapport à un sens F d'écoulement général des gaz de combustion, sensiblement parallèle à l'axe 1, orienté vers l'aval où se situe l'ouverture 5 d'échappement des gaz de combustion hors de l'enceinte 6 de la chambre de combustion.

The combustion chamber shown in FIG. 1 includes:

• an axis 1 of sensitive symmetry;
• an outer ferrule 2 having axis 1 as axis of revolution;
• an internal ferrule 3 having axis 1 as axis of revolution;
• a transverse bottom 4 connecting the two ferrules 2 and 3, disposed upstream with respect to a direction F of general flow of the combustion gases, substantially parallel to axis 1, oriented downstream where the combustion gas exhaust opening 5 is located outside the enclosure 6 of the combustion chamber.

This enclosure 6 therefore has an annular configuration with an axis 1. Regularly angularly distributed and fixed to the bottom 4, opening into the combustion enclosure 6, are arranged on the one hand, along an external circular ring, injectors of fuel 7, used for "IDLE" operation, on the other hand, along an internal circular ring, injection assemblies 8, such as those described below, used during "FULL GAS" operation , corresponding, for example, to the takeoff of an airplane. The injectors 7 are separated from the injection assemblies 8 by a median separator 9, and are connected to fuel tanks by conduits 10 and 11, respectively. Furthermore, a source of pressurized oxidizer, symbolized by the arrow G, makes it possible to supply the combustion chamber with pressurized oxidizer, to of course burn the fuel, but also used for the cooling of the various walls of the chamber. exposed to high temperatures from combustion. The pressurized oxidant source generally consists of a helical compressor placed upstream of the combustion chamber, driven by the gas turbine, which uses the combustion gases.

Figures 2 and 3 show a first embodiment of an injection assembly 4 according to the invention.

Two premix chambers 12 are delimited, each by a frustoconical wall 13, of axis A13 substantially parallel to axis 1, fixed on the bottom 4, each wall 13 converging downstream, in the direction of arrow F , having its downstream opening end 14, which opens into the combustion chamber 6. A hollow body 15, of substantially hemispherical shape, is connected to an upstream end opening 17 of each wall 13, an annular space 18 inlet (arrows H1) of oxidizer under pressure being formed between said body 15 and said wall 17. The body 15 is coaxial with the axis A13. Two pre-vaporization conduits 19 are connected, on the one hand, each to one of the bodies 15 by emerging therein coaxially through an orifice 20 for admission of a pre-evaporated oxidant / fuel mixture, on the other hand both in the case present in parallel, to a pre-vaporization chamber 21 constituted by a cylindrical wall 22 of axis A22 parallel to the axis 1. Between the end of each pre-vaporization duct 19, which ends in the orifice 20, and l upstream opening 23 of the corresponding body 15, is disposed a helical "spin" 24 for admission into the premix chamber 12 of the so-called dilution oxidizer (arrows H2). Each spin 24 has the function of rotating the oxidant passing through it, capable of promoting satisfactory homogeneity of the mixture in the premix chamber 12. Furthermore, a diaphragm 25 is placed near the end 26 through which the pre-vaporization 21 is connected to the two pre-vaporization pipes 19.

A fuel supply duct 11 is connected to a fuel injector 27, which opens inside the pre-vaporization chamber 21, towards the diaphragm 25. A protective cap 28 has a main opening 29, which surrounds, in providing an annular space 30, the downstream end 31 of the wall 22 of the pre-vaporization chamber 21, and is thus interposed between the enclosure 6 of the combustion chamber and the whole of the pre-vaporization chamber 21, of the fuel injector 27 which opens into it, and the fuel supply duct 11.

• des orifices 32, traversant la paroi de chaque corps 15, mettant en communication (flèche H3), l'espace 33, situé en arrière du fond 4 et communiquant avec la source de comburant sous pression G, avec la chambre de prémélange 12 associée audit corps 15;
• des orifices 34 ménagés dans les parties de parois 13 qui contribuent à constituer la coiffe de protection 28, et, mettant en communication (flèches H4) l'enceinte intérieure 35 de la coiffe de protection avec les chambres de prémélange 12;
• des orifices 36, ménagés dans les parties des parois 13 complémentaires des précédentes, sensiblement opposées auxdites parties qui contribuent à délimiter l'enceinte 35 de la coiffe de protection, mettant en communication l'espace 33 avec les chambres de prémélange 12 (flèches H5).

The embodiment of FIGS. 2 and 3 comprises only a single "spin" 24 associated with the orifice 20 at the end inlet of each pre-vaporization duct 19. On the other hand, the main intake of dilution oxidant is completed by the following intake ports:

• orifices 32, passing through the wall of each body 15, putting in communication (arrow H3), the space 33, located behind the bottom 4 and communicating with the source of oxidizer under pressure G, with the premix chamber 12 associated with said body 15;
• orifices 34 formed in the wall parts 13 which contribute to constituting the protective cap 28, and, putting in communication (arrows H4) the inner enclosure 35 of the protective cap with the premix chambers 12;
• orifices 36, formed in the parts of the walls 13 complementary to the previous ones, substantially opposite to said parts which contribute to delimiting the enclosure 35 of the protective cap, putting the space 33 into communication with the premix chambers 12 (arrows H5) .

• deux "vrilles" distinctes 24 et 124 entourent l'extrémité de chaque conduit 19 de prévaporisation, réalisant les communications (flèches respectives H2, H102) entre l'espace 33 et chaque chambre de prémélange 12;
• du fait de l'adjonction de deuxièmes vrilles 124, les orifices de dilution complémentaires 32, 34 et 36 de la réalisation des figures 2 et 3, ont été supprimés dans la réalisation de la figure 4;
• une enveloppe séparatrice 37, convergente, est disposée entre les deux vrilles 24 et 124, et a pour but de séparer, initialement, les débits de comburant H2, H102 qui pénètrent dans chaque chambre de prémélange 12;
• à noter que les vrilles 24, 124 sont susceptibles, selon le choix effectué, d'entraîner le comburant en rotation dans le même sens, ou, dans des sens opposés de rotation.

The embodiment of FIG. 4 is similar to that of FIGS. 2 and 3, of which it reproduces the various provisions, except for the following modifications:

• two separate "tendrils" 24 and 124 surround the end of each pre-vaporization duct 19, carrying out the communications (respective arrows H2, H102) between the space 33 and each premix chamber 12;
• due to the addition of second tendrils 124, the complementary dilution orifices 32, 34 and 36 of the embodiment of FIGS. 2 and 3 have been eliminated in the embodiment of FIG. 4;
• a separating envelope 37, convergent, is disposed between the two tendrils 24 and 124, and is intended to separate, initially, the oxidant flows H2, H102 which penetrate into each premix chamber 12;
• note that the tendrils 24, 124 are likely, depending on the choice made, to cause the oxidant to rotate in the same direction, or, in opposite directions of rotation.

Also note the communication (arrow H6), through the passage 30, of the enclosure 35 delimited by the protective cap with the space 33. Furthermore, the various walls exposed to the heat flow and to the temperature prevailing in the combustion chamber 6, can be provided, and, in the embodiments described, are provided with a multitude of small holes 38, and constitute multi-perforations for cooling said walls.

Figures 5 and 6 on the one hand, Figures 7 and 8 on the other hand, represent two combustion chambers of gas turbines, in which are used injection assemblies, as described above. The general arrangements of Figures 5 and 7 are known in themselves. It can however be noted that in both embodiments, the small size of the assemblies according to the invention, linked to the fact that a single fuel injector feeds two intake orifices of the mixture evaporated in the chambers of premix, allows optimum distribution of said intake orifices, capable of obtaining satisfactory homogeneity of the oxidant / fuel mixture admitted into the combustion chamber, and consequently capable of obtaining regular and complete combustion.

In each of the two embodiments in FIGS. 2 and 3, and in FIG. 4, it is remarkable that the protective cap 28 constitutes a screen, which protects the fuel injector 27 and the pre-vaporization chamber 21 from the high temperatures prevailing in enclosure 6 of the combustion chamber. This provision is likely to reduce or eliminate hot spots in the fuel injection area, thereby reducing or eliminating the risk of self ignition.

According to the invention, the flow of oxidant admitted into the pre-vaporization chamber 21 (arrow H6) (and its pressure) and the flow of fuel injected by the fuel injector 27 are in a ratio such that the mixture evaporated in the pre-vaporization chamber 21 and contained in the pre-vaporization conduits 19 has a richness greater than the richness of a stoichiometric mixture. This pre-evaporated mixture, admitted into the premix chambers 12, is stirred with the flow of dilution oxidant passing through the tendrils 24 and the orifices 32, 34 and 36 (arrows H2, H3, H4, H5) and the annular spaces 18 (arrows H1), as also with the oxidizer of the refrigeration multiperforations 38, the resulting mixture, contained in the premix chambers 12 having a richness lower than that of a stoichiometric mixture. Thus, the initial pre-vaporization, entirely separate from the final mixture, allows obtaining rich, pre-vaporized mixtures, sheltered from the risks of self-ignition and flashback, then a rapid, energetic injection. of the lean mixture contained in the premix chambers, towards the combustion chamber 6, which has the effect of reducing or eliminating the formation of nitrogen oxides (Nox) and of fumes, and leading to a non-polluting combustion, the downstream orientation of the orifices 20 for admission into the premix chambers 12 of the pre-evaporated mixture naturally facilitates the flow of the mixture downstream.

It should be noted that the shape converging downstream of the walls 13 of the premix chambers 12 has the effect of accelerating the propulsion of the mixture towards the combustion chamber so as to promote complete combustion of said mixture.

In the embodiment of FIG. 4, the admission of the oxidizer via the second tendrils 124 replaces the admission through the orifices 32, 34 and 36 of the embodiment of FIGS. 2 and 3.

Conventionally, the action of the tendrils 24 and 124 is to promote mixing of the mixture and to ensure good homogeneity thereof, guaranteeing the regularity of the subsequent combustion in the combustion chamber 6.

It can finally be observed that if, in the embodiments described, a fuel injector 27 is associated with two premix chambers 12, it is easy to design derived constructions in which the number of premix chambers associated with a fuel injector would be greater than two.

Similarly, the application of the invention made to fuel injection devices intended for "FULL GAS" operation can also be envisaged in the production of fuel injection devices intended for "SLOW MOTION" operation.

Furthermore, the invention is not limited to the embodiments described, but on the contrary covers all the variants which could be made to them without departing from their scope or their spirit.

Claims (14)

Fuel injection assembly intended to equip a combustion chamber of a gas turbine, comprising a fuel injector (27) opening into a pre-evaporation chamber (21) and at least two pre-evaporation conduits (19) connected to said pre-vaporization which they connect to two orifices (20) for admitting the pre-evaporated mixture into premix chambers (12) which are separate from each other and which are each separate from the pre-vaporization chamber (21) and which open into the combustion (6), the pre-vaporization chamber (21) being provided with inlet orifices (30) of an oxidizer under pre-vaporization pressure and each premix chamber (12) being provided with a device (24, 18, 32, 34, 36; 24, 124, 18) of admission of an oxidizer under dilution pressure,
characterized in that the cross-section of the orifice (s) (30) for admitting the pre-evaporating oxidant and the pressure of said pre-evaporating oxidant have values such that the pre-evaporated mixture has a higher richness than that of a stoichiometric mixture, however intake of the dilution oxidant intake device (24, 18, 32, 34, 36; 24, 124, 18) and the pressure of said dilution oxidant have values such that the mixture contained in each premix chamber has a richness lower than that of a stoichiometric mixture. An assembly according to claim 1,
characterized in that said pre-vaporization ducts (19) are connected in parallel to the pre-vaporization chamber (21), with the interposition of a diaphragm (25) between each pre-vaporization duct and the pre-vaporization chamber. An assembly according to claim 2,
characterized in that it comprises a single diaphragm (25) interposed between said pre-vaporization conduits (19) and the pre-vaporization chamber (21). An assembly according to any one of claims 1 to 3,
characterized in that the downstream being the part of the combustion chamber (6) furthest from the fuel injector (27), each orifice (20) for admitting the pre-evaporated mixture into a premix chamber (12) is oriented downstream. An assembly according to any one of claims 1 to 4,
characterized in that it comprises a protective cap (28) of the fuel injector (27) which isolates said fuel injector from the rest of the combustion chamber (6). An assembly according to claim 5,
characterized in that said protective cap (28) has a first opening (29) connected to one or more orifices (31) for admitting the pre-evaporation oxidant from the pre-evaporation chamber (21) and a second opening (29) connected to a source of oxidizer under pressure (33-G). An assembly according to claim 6,
characterized in that said first opening (29) surrounds the wall (22) of the pre-vaporization chamber (21) being spaced apart so as to provide an annular space which forms said second opening. An assembly according to any one of claims 5 to 7,
characterized in that the wall (28-13) delimiting said protective cap is provided with through orifices (34) which open into the premix chambers (12) and which constitute first orifices (34) for admitting oxidant of dilution of the mixtures contained in said premix chambers (12). Assembly according to any one of Claims 1 to 8,
characterized in that each dilution device comprises at least one helical twist (24, 124) for admitting the dilution oxidant, which is coaxial (A13) with the orifice (20) for admitting the pre-evaporated mixture. Together according to the group of the two claims 8 and 9,
characterized in that each premix chamber (12) comprises a tubular wall (13), while each dilution device comprises a single helical twist (24) and one or more second orifices (36) for admitting dilution oxidant, which pass through said wall (13) and are located substantially opposite to or to said first orifices (34) for admitting dilution oxidant. An assembly according to claim 9,
characterized in that each premix chamber (12) comprises a tubular wall (13), each dilution device comprising only two helical tendrils (24, 124). An assembly according to any one of claims 1 to 11,
characterized in that the downstream being the part of the combustion chamber furthest from the fuel injector, each premix chamber (12) has a tubular wall (13) converging downstream and a downstream orifice (14 ) of communication with the combustion chamber (6). An assembly according to claim 12,
characterized in that said tubular wall is substantially frustoconical. Assembly according to any one of claims 1 to 13,
characterized in that it is part of a fuel injection system (8) corresponding to the "FULL GAS" operation of the combustion chamber (6).

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