JP2009074798A - Fuel atomizing device of gas turbine engine - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To provide a fuel atomizing device for a gas turbine engine including a combustor to which a complex combustion system is introduced, which is formed of a combination of two lines of combustion systems, i.e. a diffusion combustion system and a lean combustion system, thus enhancing the firing performance and the flame keeping performance of the combustor, in particular, combustion stability in low load operation. <P>SOLUTION: The fuel atomizing device U of the gas turbine engine is equipped with a first fuel atomizing part 10 to atomize fuel for conducting diffused combustion and a second fuel atomizing part 20 installed in such a manner as surrounding the first fuel atomizing part 10 and atomizing the fuel for conducting premixed combustion, and characterized in that an air curtain formation part 30 for forming an air curtain to define the outer edge of a diffusive combustion region is formed between the first 10 and second fuel atomizing parts 20. <P>COPYRIGHT: (C)2009,JPO&INPIT

Description

  The present invention relates to a fuel spray device for a gas turbine engine. More specifically, the present invention relates to a fuel spray device for a gas turbine engine that can achieve more stable combustion in combined combustion that combines two combustion methods of a diffusion combustion method and a lean combustion method.

  Reducing harmful substances emitted by combustion of internal combustion engines is an urgent need for environmental conservation, but in the case of gas turbine engines, in the case of large engines, aircraft engines, etc., the pressure ratio is Along with this, the temperature and pressure at the combustor inlet have been increased, which is a factor that rather increases the amount of NOx (nitrogen oxide) that is one of the harmful substances. ing.

  For this reason, in order to reduce the amount of NOx generated in the gas turbine engine, a lean combustion method and a combustion method such as an RQL (Rich burn Quick quench Lean burn) method have been proposed. Some combustion-type gas turbine engines have been put into practical use.

  However, the lean combustion system for reducing NOx has a lack of combustion stability at low load, and in order to solve this inconvenience, the two fuel systems of the diffusion combustion system and the lean combustion system are combined. A combined combustion system has been proposed (see Patent Documents 1, 2, 3, 4, and 5).

  That is, in the lean combustion method, since a large amount of air needs to be introduced from the fuel spray device, the local fuel concentration in the combustion region becomes much thinner than the fuel concentration at the combustor outlet, and the ignitability and low load are reduced. There is a problem that the combustion performance of the is reduced. For this reason, attention has been focused on a combined combustion method that attempts to eliminate the above disadvantages by combining a diffusion combustion method and a lean combustion method that are excellent in combustion stability.

  However, in the combined combustion method, a large amount of air introduced for lean combustion affects the combustion by the diffusion combustion method, and due to the influence, in the combustion by the diffusion combustion method, sufficient ignitability, flame holding property and There is a problem that combustion stability at low load may not be obtained.

  In particular, aircraft gas turbine engines require reliable ignition under conditions of high temperature, low temperature and low pressure, and various regulations are imposed on emissions at low loads such as when idling. Therefore, a decrease in ignitability and combustion stability due to air introduced for this can be a greater problem.

Japanese Patent Laid-Open No. 5-87340 JP 2002-115847 A JP 2002-139221 A JP 2002-168449 A JP 2003-4232 A

  The present invention has been made in view of the problems of the prior art, and is characterized in that the ignitability, flame-holding property, and the like in a combustor to which a combined combustion method that combines two combustion methods of a diffusion combustion method and a lean combustion method is applied. In particular, an object of the present invention is to provide a fuel spray device for a gas turbine engine that can improve combustion stability at low load.

  A fuel spray device for a gas turbine engine according to the present invention is provided with a first fuel spray portion spraying fuel for diffusion combustion, and surrounding the first fuel spray portion, and sprays fuel for premixed combustion. An air curtain for defining an outer edge of a diffusion combustion region between the first fuel spray portion and the second fuel spray portion. An air curtain forming part for forming the film is provided.

  In the fuel spray device for a gas turbine engine of the present invention, the first fuel spray portion has a cylindrical main body having a double wall structure for injecting fuel for diffusion combustion, and an inner swirler disposed in the main body. The spray nozzle preferably defines a fuel spray angle from the cylindrical body, and an outswarr disposed between the cylindrical body and the spray nozzle.

  In the fuel spray device for a gas turbine engine according to the present invention, the first fuel spray portion includes a bottomed cylindrical main body that injects fuel for diffusion combustion, and a divergent spread that is externally fitted to the bottomed cylindrical main body. Nozzle-shaped cylindrical inner peripheral wall, divergent nozzle-shaped cylindrical intermediate wall disposed outside the cylindrical inner peripheral wall, and divergent nozzle-shaped nozzle disposed outside the cylindrical intermediate wall A spray nozzle, an inner swirler disposed between the cylindrical inner peripheral wall and the cylindrical intermediate wall, and an outer swirler disposed between the cylindrical intermediate wall and the spray nozzle. Preferably it is. In that case, it is more preferable that the influence of the inner swirler is made smaller than the influence of the outer swirler.

  Furthermore, in the fuel spray device for a gas turbine engine of the present invention, it is preferable that the air injection port of the air curtain forming portion is provided on the outer edge of the spray nozzle.

  Furthermore, in the fuel spray device for a gas turbine engine according to the present invention, it is preferable that the second fuel spray portion has a premixing preliminary chamber and a premixing chamber.

  Further, in the fuel spray device for a gas turbine engine according to the present invention, the fuel spray portion includes an inner block including the fuel injection portion and an outer block not including the fuel injection portion, and the inner block and the outer block are included. It may be separable, or the inner block and the outer block may be integrated.

  Thus, this fuel spray device is provided in the combustor.

  Since the fuel spray device for a gas turbine engine of the present invention is configured as described above, the ignitability in a combustor to which a combined combustion method in which two combustion methods of a diffusion combustion method and a lean combustion method are combined is applied, An excellent effect is obtained that the flame holding ability and particularly the combustion stability at a low load can be improved.

It is the schematic which shows the fuel spray apparatus of the gas turbine engine which concerns on Embodiment 1 of this invention in a partial cross section. It is detail drawing shown in the partial cross section of the fuel spraying apparatus. It is a schematic diagram which shows the spray pattern of the fuel by the fuel spray apparatus. It is a rear view which shows the detail of the base of the fuel spraying apparatus. It is detail drawing which shows a mode that the fuel spray apparatus was isolate | separated by the separable part in a partial cross section. It is a front view in FIG. It is FIG. 2 equivalent view of Embodiment 2 of this invention. It is FIG. 2 equivalent view of Embodiment 3 of this invention. It is FIG. 2 equivalent view of Embodiment 4 of this invention. It is FIG. 2 equivalent view of Embodiment 5 of this invention. It is FIG. 2 equivalent view of Embodiment 6 of this invention. It is FIG. 2 equivalent view of Embodiment 7 of this invention.

  Hereinafter, although the present invention is explained based on an embodiment, referring to an accompanying drawing, the present invention is not limited only to this embodiment.

Embodiment 1
FIG. 1 is a partial cross-sectional view of a fuel spray device for a gas turbine engine according to Embodiment 1 of the present invention. In FIG. 2, the principal part enlarged view is shown. FIG. 3 schematically shows a spray pattern by the fuel spray device.

  The fuel spraying device U is generally provided in a combustor of a gas turbine engine (not shown), and as shown in FIG. 1, the fuel from the first fuel supply system F1 for diffusion combustion is supplied to the diffusion combustion region A1 ( The fuel from the second fuel supply system F2 for lean combustion is provided outside the radial direction so as to surround the first fuel spraying portion 10 and the first fuel spraying portion 10 spraying toward the first fuel spraying portion 10) And a second fuel spray section 20 that sprays the premixed combustion area A2 (see FIG. 3) and an air curtain forming section 30 that forms an air curtain that defines the outer edge of the diffusion combustion area A1. It is supposed to be.

  Here, since the fuel spraying device U has a generally axial structure, the reference numerals in the figure are attached only to the upper half in principle.

  Hereinafter, the 1st fuel spraying part 10 is demonstrated.

  As shown in FIG. 2, the first fuel spray section 10 is formed of an inner cylindrical body 11 and an outer cylindrical body 12. The first fuel spray section 10 is located in the center and has a cylindrical double wall main body 13 that supplies fuel for diffusion combustion. A venturi nozzle-like spray nozzle 14 arranged concentrically outside the main body 13, an inner swirler 15 arranged annularly in the inner cylindrical body 11, and the outer cylindrical body 12 and the spray nozzle 14. An outer swirler 16 disposed therebetween, and a fuel supply passage 13b for sending fuel from the first fuel supply system F1 to an injection port 13a provided on the inner surface of the downstream end of the main body 13 is an inner cylindrical body. 11 and the outer cylindrical body 12. And the 1st fuel spraying part 10 injects the fuel supplied by the fuel supply path 13b from the injection port 13a, atomizes the injected fuel with the air from the inner swirler 15 (primary atomization), and primary The atomized fuel is further atomized (secondary atomization) by the swirling airflow from the outer swirler 16 in the spray nozzle 14 and sprayed in the form of a mist in the combustion chamber.

  Here, the main body 13 is supported by the base 40 (see FIG. 4) connected to the fuel pipe T (see FIG. 1) of the first fuel supply system F1 together with the main body 24 of the second fuel spraying section 20 described later. Has been.

  The shape and attachment position of the spray nozzle 14 are adjusted so that the fuel injected from the injection port 13a has a predetermined spread angle. That is, the cylindrical portion 14a is positioned downstream of the outer cylindrical body 12, and the minimum inner diameter portion (throttle portion) 14b is set at a predetermined position on the downstream side of the injection port 13a. The angle is set to a predetermined angle.

  The outer swirler 16 is disposed between the cylindrical portion 14 a of the spray nozzle 14 and the outer cylindrical body 12.

  As shown in FIG. 2, the fuel injected from the injection port 13a is inclined toward the central axis of the main body 13 because the downstream portion 12a of the outer cylindrical body 12 has a tapered truncated cone shape. Is sprayed into a film. The fuel injected in the form of a film is atomized by the air from the inner swirler 15 and injected from the outlet 13c, and further atomized and atomized in the spray nozzle 14 by the swirling airflow from the outer swirler 16. Sprayed into the combustion chamber.

  Next, the second fuel spray unit 20 will be described.

  As shown in FIG. 2, the second fuel spray section 20 includes an inner cylindrical body 21 and an outer cylindrical body 22, and an upstream end portion by a lid-shaped section 23 of the base 40 outside the spray nozzle 14. A cylindrical double-walled main body 24 for supplying premixed combustion fuel, the opening of which is closed and supported by the base 40, a cylindrical intermediate wall 25 arranged concentrically outside the main body 24, and a cylindrical shape A cylindrical outer peripheral wall 26 concentrically disposed outside the intermediate wall 25, a cylindrical partition wall 27 that partitions the cylindrical intermediate wall 25 and the cylindrical outer peripheral wall 26, and the cylindrical intermediate wall 25 and the cylindrical shape An inner swirler 28 disposed in the premixing preparatory chamber 41 between the partition wall 27 and an outer swirler 29 disposed between the cylindrical partition wall 27 and the cylindrical outer peripheral wall 26; Fuel from the system F2 is drilled at a predetermined interval on the outer periphery on the downstream side of the outer cylindrical body 22. A fuel feed path 24a for feeding to the injection port 22a is formed in the gap between the inner cylindrical body 21 and the outer cylindrical body 22, and the premixing chamber 42 is formed by the cylindrical intermediate wall 25 and the cylindrical outer peripheral wall 26. The fuel which is defined and is fed by the fuel feed path 24a is injected from the injection port 22a into the premixing preliminary chamber 41, and the injected fuel is atomized (primary atomization) with air from the inner swirler, and atomized. The mixed fuel is premixed and sprayed into the combustion chamber while being further atomized (secondary atomization) by the swirling airflow from the outer swirler 29 in the premixing chamber 42.

  Here, the inner diameter of the inner cylindrical body 21 is made larger than the outer diameter of the cylindrical portion 14a of the spray nozzle 14, as shown in FIG. 2, and between the inner cylindrical body 21 and the cylindrical portion 14a of the spray nozzle 14. An air introduction path 31 of the air curtain forming unit 30 is formed.

  As shown in FIG. 2, the cylindrical intermediate wall 25 is configured to cover substantially half (downstream part) of the outer cylindrical body 22, and its downstream end coincides with the downstream end of the spray nozzle 14. It has been. In addition, an inlet 25 a is provided at a position corresponding to the injection port 22 a of the cylindrical intermediate wall 25 in order to introduce the injected fuel into the premixing preliminary chamber 41.

  Here, the cylindrical intermediate wall 25 and the outer cylindrical body 22 are fastened to each other by, for example, a predetermined number of pins B, and the cylindrical intermediate wall 25 and the outer cylindrical body are removed by removing the pins B. 22 can be released.

  The cylindrical intermediate wall 25 and the cylindrical partition wall 27 are connected via an inner swirler 28, and the cylindrical partition wall 27 and the cylindrical outer peripheral wall 26 are connected via an outer swirler 29, and the cylindrical intermediate wall 25 is further connected to the spray nozzle 14 via a lid member 33, and each of these connected members forms one block (hereinafter referred to as an outer block) OP. The outer block OP can be separated from the inner block IP described later by releasing the fitting between the cylindrical intermediate wall 25 and the outer cylindrical body 22.

  The cylindrical partition wall 27 has its upstream end aligned with the upstream end of the cylindrical intermediate wall 25 and its length adjusted so that the downstream end is positioned a predetermined distance downstream of the inlet 25a. .

  The cylindrical outer peripheral wall 26 is stepped with the upstream end positioned a predetermined distance downstream from the upstream end of the cylindrical partition wall 27, and the downstream end coincides with the downstream end of the cylindrical intermediate wall 25. It has been made. An attachment portion 26a for attaching the fuel spray device U to the combustor is formed in a bowl shape on the downstream side portion of the cylindrical outer peripheral wall 26.

  The inner swirler 28 is provided on the upstream side portion between the cylindrical intermediate wall 25 and the cylindrical partition wall 27.

  The outer swirler 29 is provided on the upstream side portion between the cylindrical partition wall 27 and the cylindrical outer peripheral wall 26.

  Thus, the fuel injected from the injection port 22a and introduced into the premixing preparatory chamber 41 through the introduction port 25a is atomized (primary atomization) by the airflow from the inner swirler 28 and then further swirled by the swirl airflow from the outer swirler 29. It is atomized (secondary atomization), premixed in the premixing chamber 42, and sprayed into the combustion chamber.

  Next, the air curtain forming unit 30 will be described.

  As shown in FIG. 2, the air curtain forming unit 30 includes a storage chamber 32 defined by the spray nozzle 14 and the cylindrical intermediate wall 25, and downstream end portions of the spray nozzle 14 and the cylindrical intermediate wall 25. A ring-shaped lid member 33 is provided.

  Here, as shown in FIG. 2, an air flow path 34 is formed in the lid member 33 from the inner surface of the upstream outer peripheral portion to the outer surface of the downstream inner peripheral portion (the surface facing the combustion chamber). That is, the air flow path 34 which has the air introduction port 33a in the upstream outer peripheral part inner surface and the air injection port 33b in the downstream inner peripheral part outer surface is formed. The lid member 33 is air-cooled by the air flow path 34 and air curtain forming air is supplied into the combustion chamber.

  Thus, the air introduced into the storage chamber 32 from the air introduction path 31 formed between the spray nozzle 14 and the inner cylindrical body 21 is injected into the combustion chamber from the air injection port 33b while cooling the lid member 33. To form an air curtain. Due to this air curtain, the fuel sprayed from the spray nozzle 14 to the diffusion combustion flow area A1 in the combustion chamber becomes like pattern P, and its spread is restricted, so that the fuel is mixed with the air in the premixing area A2. There is nothing (see FIG. 3). The sprayed fuel is further atomized (tertiary atomization) by the air forming the air curtain. Therefore, stable diffusion combustion is achieved. The achievement of this stable diffusion combustion is made more reliable because the air injection port 33b for air curtain forming air is located at a predetermined distance L from the inner end of the premixing chamber 42.

  Next, the base 40 will be described. FIG. 4 shows a rear view of a part of the fuel spraying device U.

  As shown in FIG. 4, the base 40 includes an inner support portion 40 a that is a small-diameter ring-shaped member for supporting the main body 13 of the first fuel spray portion 10, and an upstream side of the main body 24 of the second fuel spray portion 20. The lid-shaped portion 23 is a large-diameter ring-shaped member for closing the end opening and supporting the main body 24. An inner swirler vent hole 40b is provided in the center of the inner support portion 40a, and an outer swirler vent hole 40d, 40d divided by the connecting portions 40c, 40c between the inner support portion 40a and the lid-like portion 23. Is provided.

  Thus, the base 40 is connected to the main body 13 of the first fuel spraying unit 10 and the main body 24 of the second fuel spraying unit 20 to form one connecting body (hereinafter referred to as an inner block) IP, As described above, by releasing the fitting between the cylindrical intermediate wall 25 and the outer cylindrical body 22, the inner block IP and the outer block OP not including the fuel injection portion can be separated.

  FIG. 5 shows the inner block IP separated from the outer block OP. FIG. 6 shows a front view thereof.

  With this configuration, it is possible to perform maintenance or the like by removing only the inner block IP from a combustor casing (not shown). In addition, the space provided in the combustor casing for extraction is only required for the inner block IP, and as a result, the weight of the combustor casing can be reduced.

  As described above, according to the first embodiment, in the combustor to which the so-called combined combustion method in which the two combustion methods of the diffusion combustion method and the lean combustion method are combined, the ignitability, the flame holding property, and the low load are applied. The combustion stability at the time can be improved. In addition, the combustor can be reduced in size and weight.

Embodiment 2
FIG. 7 shows a fuel spray device U1 according to Embodiment 2 of the present invention. The second embodiment is obtained by modifying the first embodiment, and is a modification of the first fuel spray unit 10 for diffusion combustion. Since the configuration other than the first fuel spray unit 10A is the same as that of the first embodiment, the reference numerals are used and the detailed description is omitted.

  Hereinafter, the first fuel spray unit 10A will be described.

  As shown in FIG. 7, the first fuel spray section 10 </ b> A includes a bottomed cylindrical main body 51 that supplies fuel for diffusion combustion, a cylindrical inner peripheral wall 52 that is externally fitted to the main body 51, and a cylindrical inner peripheral wall. 52, a cylindrical intermediate wall 53 arranged concentrically outside, a venturi nozzle-like spray nozzle 54 arranged concentrically outside the cylindrical intermediate wall 53, a cylindrical inner peripheral wall 52, and a cylindrical intermediate wall 53. And an outer swirler 56 disposed between the cylindrical intermediate wall 53 and the spray nozzle 54, and a first fuel supply system F1 at the downstream end of the main body 51. The injection port 51a which injects the fuel supplied in the inside of the main body 51 from is formed. Then, the first fuel spray unit 10A injects the fuel fed into the main body 51 from the injection port 51a, atomizes the injected fuel with air from the inner swirler 55 (primary atomization), and primary atomization. The fuel is further atomized (secondary atomization) by the swirling airflow from the outer swirler 56 in the spray nozzle 54 and sprayed in the combustion chamber in the form of a mist.

  Here, the main body 51 is supported by the base 40 together with the main body 24 of the second fuel spraying section 20, and the main body 51 of the first fuel spraying section 10A, the main body 24 of the second fuel spraying section 20 and the base 40 are connected to the inner block IP. Is forming. The cylindrical inner peripheral wall 52, the cylindrical intermediate wall 53, and the venturi nozzle-like spray nozzle 54 are connected to the cylindrical intermediate wall 25 together with the cylindrical outer peripheral wall 26 to form an outer block OP.

  As described above, also in the second embodiment, the inner block IP and the outer block OP can be separated by releasing the fitting between the cylindrical intermediate wall 25 and the outer cylindrical body 22. Similar effects can be obtained.

  Further, the cylindrical inner peripheral wall 52 and the cylindrical intermediate wall 53 are formed in a divergent nozzle shape having constricted portions 52a and 63a corresponding to the constricted portions 54a of the spray nozzle 54 in order to prevent a rapid contraction of the flow path. Is formed. An introduction port 52 b for introducing fuel into a space defined by the cylindrical inner peripheral wall 52 and the cylindrical intermediate wall 53 is provided at a location corresponding to the injection port 51 a of the cylindrical inner peripheral wall 52.

  As shown in FIG. 7, the upstream end of the cylindrical intermediate wall 53 is made to coincide with the upstream end of the cylindrical inner peripheral wall 52, and the downstream end is downstream by a predetermined distance from the downstream end of the cylindrical inner peripheral wall 52. The length is adjusted to be located in the spray nozzle 54 on the side.

  As shown in FIG. 7, the upstream end of the spray nozzle 54 is stepped by being positioned a predetermined distance downstream from the upstream end of the cylindrical intermediate wall 53.

  The inner swirler 55 is provided on the upstream side portion between the cylindrical inner peripheral wall 52 and the cylindrical intermediate wall 53.

  The outer swirler 56 is provided on the upstream side portion between the cylindrical intermediate wall 53 and the cylindrical portion 54 b of the spray nozzle 54.

  Thus, the fuel injected from the injection port 51 a and introduced into the space (primary atomization space) 57 defined by the cylindrical inner peripheral wall 52 and the cylindrical intermediate wall 53 from the introduction port 52 a is an air flow from the inner swirler 55. Is atomized (primary atomization), and further atomized (secondary atomization) by the swirling airflow from the outer swirler 56, and sprayed into the combustion chamber.

  Hereinafter, it is the same as that of Embodiment 1.

  As described above, according to the second embodiment, a so-called combined combustion method in which two combustion methods of a diffusion combustion method and a lean combustion method are combined while simplifying the configuration of the first fuel spray unit 10A is applied. In the combustor, the ignitability, flame holding ability and combustion stability at low load can be improved.

Embodiment 3
FIG. 8 shows a fuel spray device U2 according to Embodiment 3 of the present invention. The third embodiment is a modification of the second embodiment, and is a modification of the first fuel spray section 10A for diffusion combustion. That is, in the first fuel spraying part 10B, the upstream end of the cylindrical inner peripheral wall 52 and the cylindrical intermediate wall 53 is made to coincide with the upstream end of the spray nozzle 54, and the influence of the inner swirler 55 is reduced, that is, the turning force. It is made by reducing.

  In addition, since it is the same as that of Embodiment 2 of the other structure and an effect | action and effect, the detailed description is abbreviate | omitted.

  Thus, in the third embodiment, since the influence of the inner swirler 55 is reduced, the angle control of the sprayed fuel by the spray nozzle 54 is more reliably performed, and as a result, more stable diffusion combustion is achieved.

Embodiment 4
FIG. 9 shows a fuel spray device U3 according to Embodiment 4 of the present invention. The fourth embodiment is a modification of the third embodiment, in which the second fuel spraying unit 20 and the air curtain forming unit 30 are modified.

  That is, in the second fuel spray section 20, the diameter of the cylindrical intermediate wall 25A is made constant, and the premixing chamber 42A is formed with a constant width. Thereby, the shape of each member becomes simple and the manufacture becomes easy.

  In the air curtain forming portion 30A, as the diameter of the cylindrical intermediate wall 25A is made constant, the distance L1 between the inner end of the premixing chamber 42A and the air injection port 33Ab for air curtain forming air is set. While being shorter than the distance L in the third embodiment, the storage chamber 32A is made smaller. Therefore, the radial width of the air curtain forming portion 30 is reduced, and the fuel spray device U3 can be easily reduced in size.

  On the other hand, by reducing the distance L1, the air introduced for lean combustion tends to affect diffusion combustion. However, if the influence can be sufficiently suppressed only by the air curtain formed by the air curtain forming unit 30 even if the distance L1 is reduced according to the required specifications of the gas turbine, the second fuel spray unit 20 and the The air curtain forming unit 30 is preferably configured in terms of ease of manufacturing and downsizing of the apparatus.

  In addition, since the other structure and the effect | action and effect are the same as that of Embodiment 3, the detailed description is abbreviate | omitted.

  As described above, in the fourth embodiment, the distance L1 between the inner end of the premixing chamber 42A and the air injection port 33Ab for air curtain forming air is reduced, so that the fuel spray device can be easily downsized. In addition, since the shape of the cylindrical intermediate wall 25A becomes simple, the design and manufacture thereof are facilitated.

Embodiment 5
FIG. 10 shows a fuel spray device U4 according to Embodiment 5 of the present invention. The fifth embodiment is obtained by modifying the first embodiment. The second fuel spray unit 20 and the air curtain forming unit 30 are modified, and the outer block OP and the inner block IP are integrated. is there.

  That is, in the second fuel spray section 20B, the fuel supply path 24Ba is defined by the integrally formed inner cylindrical body 21B and the cylindrical intermediate wall 25B, and the outer cylindrical body 22 in the first embodiment. Is omitted. For this reason, the fuel fed through the fuel feed path 24Ba is directly introduced into the premixing preliminary chamber 41B from the injection port 22a. As in the fourth embodiment, the diameter of the cylindrical intermediate wall 25B is constant.

  Here, since the outer block OP and the inner block IP are integrated, the cylindrical outer peripheral wall 26B is not provided with a hook-shaped attachment portion.

  Further, in the air curtain forming part 30B, the distance L2 between the inner end of the premixing chamber 42B and the air injection port 33Bb for air curtain forming air as the diameter of the cylindrical intermediate wall 25B is made constant. Is shorter than the distance L in the first embodiment. The advantages and disadvantages of making the distance L2 shorter than the distance L in the first embodiment are the same as those in the fourth embodiment.

  In addition, since the other structure and the effect | action and effect are the same as that of Embodiment 1, the detailed description is abbreviate | omitted.

  Thus, in the fifth embodiment, the outer cylindrical body 22 is omitted, and the inner cylindrical body 21B and the cylindrical intermediate wall 25B that define the fuel supply path 24Ba are integrally formed. Unlike Embodiments 1 to 4, the outer block OP and the inner block IP cannot be separated. However, since the number of parts is thereby reduced, the fuel spray device can be easily manufactured and the cost can be reduced.

Embodiment 6
FIG. 11 shows a fuel spray device U5 according to Embodiment 6 of the present invention. The sixth embodiment is obtained by modifying the third embodiment, and is obtained by modifying the second fuel spray unit 20 and the air curtain forming unit 30 in the same manner as in the fifth embodiment.

  That is, in the second fuel spray section 20B, the fuel supply path 24Ba is defined by the integrally formed inner cylindrical body 21B and the cylindrical intermediate wall 25B, and the outer cylindrical body 22 in the third embodiment. Is omitted. As in the fourth embodiment, the diameter of the cylindrical intermediate wall 25B is constant.

  Here, since the outer block OP and the inner block IP are integrated, the cylindrical outer peripheral wall 26B is not provided with a hook-shaped attachment portion.

  Further, in the air curtain forming part 30B, the distance L2 between the inner end of the premixing chamber 42B and the air injection port 33Bb for air curtain forming air as the diameter of the cylindrical intermediate wall 25B is made constant. Is shorter than the distance L in the third embodiment. The advantages and disadvantages of making the distance L2 shorter than the distance L in the first embodiment are the same as those in the fourth embodiment.

  In addition, since it is the same as that of Embodiment 3 of the other structure and an effect | action and effect, the detailed description is abbreviate | omitted.

  As described above, in the sixth embodiment, as in the fifth embodiment, the outer cylindrical body 22 is omitted, and the inner cylindrical body 21B and the cylindrical intermediate wall 25B that define the fuel supply path 24Ba are integrally formed. Therefore, unlike the first to fourth embodiments, the outer block OP and the inner block IP cannot be separated. However, this reduces the number of parts, which facilitates the manufacture of the fuel spray device.

Embodiment 7
FIG. 12 shows a fuel spraying device U6 according to Embodiment 7 of the present invention. In the seventh embodiment, the third embodiment is modified and the outer block OP and the inner block IP are integrated.

  That is, in the first fuel spray section 10C, the cylindrical inner peripheral wall 52C, the cylindrical intermediate wall 53C, and the injection nozzle 54C are not divergent but have a constant diameter.

  In the second fuel spray section 20B, as in the fifth and sixth embodiments, the fuel feed path 24Ba is defined by the integrally formed inner cylindrical body 21B and the cylindrical intermediate wall 25B. The outer cylindrical body 22 of the third embodiment is omitted. As in the fourth embodiment, the diameter of the cylindrical intermediate wall 25B is constant.

  Here, since the outer block OP and the inner block IP are integrated, the cylindrical outer peripheral wall 26B is not provided with a hook-shaped attachment portion.

  In the air curtain forming portion 30C, the circumferential cross-sectional shape of the storage chamber 32C is a simple rectangle as the diameters of the injection nozzle 54C and the cylindrical intermediate wall 25B are constant. Further, the distance L3 between the inner end of the premixing chamber 42B and the air injection port 33Cb for air curtain forming air is made shorter than the distance L in the third embodiment. Advantages and disadvantages resulting from making this distance L3 shorter than the distance L in the first embodiment are the same as in the fourth embodiment.

  In addition, since it is the same as that of Embodiment 3 of the other structure and an effect | action and effect, the detailed description is abbreviate | omitted.

  As described above, in the seventh embodiment, the cylindrical inner peripheral wall 52C, the cylindrical intermediate wall 53C, and the injection nozzle 54C are not divergent but have a constant diameter, and the inner cylindrical body 21B and the cylindrical intermediate wall 25B are integrally formed. Since they are formed, the shape of each part is simplified, the manufacturing is facilitated, and the number of parts can be reduced.

  The present invention can be applied to a combustor to which a combined combustion method in which two combustion methods of a diffusion combustion method and a lean combustion method are combined is applied.

DESCRIPTION OF SYMBOLS 10 1st fuel spraying part 13 Main body 13a Injection port 14 Spraying nozzle 15 Inner swirler 16 Outer swirler 20 Second fuel spraying part 24 Main body 28 Inner swirler 29 Outer swirler 30 Air curtain formation part 31 Air introduction path 32 Reservoir chamber 33 Lid member 34 Air flow path 41 Premixing preliminary chamber 42 Premixing chamber U Fuel spray device A1 Diffusion combustion zone A2 Premixing combustion zone P Spray pattern F1 First fuel supply system F2 Second fuel supply system IP Inner block OP Outer block

Claims (9)

A gas comprising a first fuel spraying part for spraying fuel for diffusion combustion and a second fuel spraying part provided to surround the first fuel spraying part and spraying fuel for premixed combustion A fuel spray device for a turbine engine,
A fuel for a gas turbine engine, wherein an air curtain forming part for forming an air curtain for defining an outer edge of a diffusion combustion region is provided between the first fuel spray part and the second fuel spray part. Spraying equipment.   The first fuel spraying section defines a cylindrical main body having a double wall structure for injecting fuel for diffusion combustion, an inner swirler disposed in the main body, and a fuel spray angle from the cylindrical main body. The fuel spray device for a gas turbine engine according to claim 1, further comprising: a spray nozzle that performs an operation, and an outer swirler disposed between the cylindrical main body and the spray nozzle.   The first fuel spraying portion has a bottomed cylindrical main body that injects fuel for diffusion combustion, a divergent nozzle-shaped cylindrical inner peripheral wall that is externally fitted to the bottomed cylindrical main body, and the cylindrical inner peripheral wall A nozzle-shaped cylindrical intermediate wall that is arranged outwardly, a nozzle-shaped spray nozzle that is arranged outwardly of the cylindrical intermediate wall, the cylindrical inner peripheral wall, and the cylindrical intermediate wall The gas turbine engine according to claim 1, further comprising an inner swirler disposed between a wall and an outer swirler disposed between the cylindrical intermediate wall and the spray nozzle. Fuel spray device.   4. The fuel spray device for a gas turbine engine according to claim 3, wherein the influence of the inner swirler is less than the influence of the outer swirler.   4. The fuel spray device for a gas turbine engine according to claim 2, wherein an air injection port of the air curtain forming portion is provided at an outer edge of the spray nozzle.   The fuel spray device for a gas turbine engine according to claim 1, wherein the second fuel spraying section includes a premixing preliminary chamber and a premixing chamber.   2. The fuel spraying portion is composed of an inner block including a fuel injection portion and an outer block not including a fuel injection portion, and the inner block and the outer block are separable. Gas turbine engine fuel spray device.   2. The fuel spray unit includes an inner block including a fuel injection unit and an outer block including no fuel injection unit, and the inner block and the outer block are integrated. Fuel spray device for gas turbine engines.   A combustor comprising the fuel spray device for a gas turbine engine according to any one of claims 1 to 8.

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