JP4477038B2 - Combustion device for gas turbine engine - Google Patents

Description

  The present invention relates to a combustion apparatus for a gas turbine engine having a fuel injection structure of a combined combustion system that combines two combustion systems of a diffusion combustion system and a lean premixed combustion system.

In a gas turbine engine, in consideration of environmental protection, combustion and strict environmental standards are provided with respect to the composition of the exhaust gas discharged by the nitrogen oxides (hereinafter, referred to as N0 _X) to reduce the harmful substances such as It has been demanded. On the other hand, for large gas turbines and aircraft engines, pressure ratios tend to be set higher due to demands for lower fuel consumption and higher output, and accordingly, higher temperatures and higher pressures are being introduced at the combustion equipment inlet. Since the combustion temperature tends to increase due to the increase in the inlet temperature of the combustion apparatus, there is a concern that N0 _X may be rather increased.

Therefore, in recent years, a lean pre-mixture combustion system that can effectively reduce the N0 _X emissions, the composite combustion system combining the combustion method of the two systems of excellent diffusion combustion system ignition performance and the flame holding performance are proposed ing. In the lean premixed combustion method, air and fuel are premixed and burned as a mixture with uniform fuel concentration, so there is no combustion region where the flame temperature is locally high, and the fuel is diluted. by the ability to lower the flame temperature in whole, although there is an advantage that can be effectively reduced N0 _X emissions, admixing uniformly a large amount of air and fuel, very local fuel concentration in the combustion region There is a problem that the fuel becomes thinner and lowers the combustion stability particularly at low load. On the other hand, the diffusion combustion method has an advantage of excellent flame holding performance because the fuel and air are burned while being diffused and mixed, so that the blow-off hardly occurs even at low loads. Accordingly, the composite combustion system, as well as can hold the combustion stability by diffusion combustion during starting and low load can be reduced N0 _X emissions by the lean premixed mixture combustion at high loads.

  The combustion apparatus based on the combined combustion system forms a fuel injection portion for spraying fuel so as to form a diffusion combustion area based on a diffusion combustion system in the combustion chamber, and a premix combustion area based on a lean premixed gas combustion system within the combustion chamber. A premixed gas supply unit that supplies a premixed gas of fuel and air is provided. This combustion apparatus supplies fuel from only the fuel injection unit at the time of start-up or low load, and supplies fuel from the premixed gas supply unit in addition to the fuel injection unit at high load. (Patent Documents 1 and 2).

JP 2002-115847 A JP 2002-139221 A

  Meanwhile, high-temperature and high-pressure compressed air supplied from the compressor is introduced from the annular diffuser to the upstream side of the annular combustion cylinder at a flow rate of about 100 m / sec. About 15% is only taken into the combustion chamber via the axial flow swirler, but in the above-described combined combustion system, 50% to 70% of the introduced compressed air is put into the combustion chamber via the fuel injection unit. Therefore, an axial flow swirler having a large outer diameter is used for the premixed gas supply unit outside the fuel injection unit. A circular opening having a diameter corresponding to the axial flow swirler having a large outer diameter is formed in the cowl covering the upstream side of the combustion cylinder, and the compressed air is guided to the fuel injection unit through the opening. . In the case of the conventional diffusion combustion system, the circular opening is set to have a diameter of about 1.2 to 2 times the opening flow path height of the diffuser. The diameter is set to be 3 to 4 times the road height.

  However, the high-temperature and high-pressure compressed air introduced from the annular diffuser to the upstream side of the cowl is annular with a width corresponding to the height of the opening of the diffuser, that is, the radial dimension of the air inlet to the combustion device. A high dynamic pressure region distributed in a band shape is formed, and this high dynamic pressure region faces only the central portion of each opening having a large diameter of the cowl. Therefore, the axial swirler of the premixed gas supply unit includes a portion into which high dynamic pressure compressed air that has passed through the central portion in the gas turbine radial direction at the opening of the cowl flows and a portion into which compressed air that does not have high dynamic pressure flows. And the distribution of the air flow rate passing through the axial swirler becomes non-uniform.

  In this way, when air passes through the axial swirler with a non-uniform flow distribution, uneven mixing of fuel and air occurs in the premixing passage of the premixed gas supply section, so the flame temperature in the combustion chamber is nonuniform. This causes an adverse effect such as an increase in the amount of NOx generated in the high-temperature flame part, a decrease in the life of the liner due to the generation of hot spots on the liner, and a decrease in the life of the turbine due to uneven distribution of the outlet temperature of the combustor. In addition, if the air velocity distribution derived from the axial swirler is uneven, a good backflow region cannot be formed in the combustion chamber, which hinders good ignitability and stable combustion, and reduces combustion efficiency. Invite.

  In order to solve the above-mentioned problem, it is conceivable to install the cowl far away from the diffuser or to increase the opening channel height of the diffuser, but when using any of these means, Since the combustor's axial length increases and the combustor becomes larger, it is difficult to adopt.

  The present invention relates to a combined combustion system that combines two combustion systems, ie, a diffusion combustion system and a lean premixed combustion system, to uniformize the flow distribution of air flowing into the air intake port of the premixed gas supply section, and to form a combustion chamber. An object of the present invention is to provide a combustion apparatus for a turbine engine that can make the flame temperature distribution of the turbine uniform.

  In order to achieve the above object, a combustion apparatus for a gas turbine engine according to the present invention includes an annular combustion cylinder that forms a combustion chamber, and a premixed fuel and air that forms a premixed gas combustion region in the combustion chamber. A plurality of fuel injection units having a pre-mixture supply section for supplying a mixture, a fuel supply unit for supplying fuel to the pre-mixture supply section, and compressed air from a compressor upstream of the fuel injection unit. An annular air introduction port to be introduced, and a cover portion positioned on the upstream side in the axial direction with respect to the annular air intake port in the premixed gas supply portion, and the cover portion from the air intake port to the It is spaced apart on the upstream side in the axial direction to form an air introduction path between the air intake and at least partly overlaps the air intake as viewed from the axial direction.

  According to this configuration, the cover portion positioned on the upstream side in the axial direction of the annular air intake of the premixed gas supply portion partially overlaps the air intake as viewed from the axial direction, so that the region having a high dynamic pressure is obtained. As a result, the compressed air can be allowed to flow at a uniform flow rate throughout the air intake. Thereby, in the premixed gas supply part, the mixed concentration of fuel and air is made uniform throughout. As a result, since the flame temperature in the combustion chamber becomes uniform, the amount of NOx generated due to the high temperature flame can be suppressed, and hot spot generation on the wall surface of the liner constituting the combustion chamber can be prevented, and the liner can be prevented. A sufficient life can be ensured. In addition, a sufficient life of the turbine can be ensured as the outlet temperature distribution of the combustor becomes uniform. Furthermore, since the velocity distribution of the air-fuel mixture supplied from the pre-air mixture supply unit is made uniform, a good backflow region can be stably formed in the combustion chamber, so that stable combustibility, good ignition performance and high combustion efficiency are achieved. Can be secured.

  In the present invention, the fuel injection unit further includes a fuel injection unit that sprays fuel so as to form a diffusion combustion region in the combustion chamber, and the fuel injection unit is a central part of the annular premixed gas supply unit The main part of the fuel supply unit is arranged upstream of the air intake, and is located at the center of the annular main fuel supply that is concentric with the air intake. The fuel injection unit may have a pilot fuel supply unit that supplies pilot fuel. As a result, the fuel injection unit and the premixed gas supply unit can be appropriately arranged to reduce the size of the fuel injection unit.

  The present invention further includes a cowl that covers the upstream end portion of the combustion cylinder and guides compressed air upstream of the fuel injection unit to the outside of the combustion cylinder, and the cowl introduces air into the fuel injection unit. It is preferable to have an opening and to integrally form the cover part on the cowl. Thereby, since a cover part can be formed only by changing the hole shape of the opening of the existing cowl in a combustion apparatus, the increase in a number of parts can be suppressed and it can be set as an inexpensive structure.

  In the configuration in which the cover is integrally formed with the cowl, the fuel supply unit is disposed on the upstream side of the air intake and includes the annular main fuel supply that is concentric with the air intake, and the cover It is preferable that the portion is formed on both side portions of the opening in the cowl facing the gas turbine circumferential direction. The compressed air introduced from the air inlet forms a high dynamic pressure region extending in the shape of an annular belt in the circumferential direction of the gas turbine, so that cover portions are integrally formed on both sides of the cowl opening facing the circumferential direction of the gas turbine. Thus, the cover portion can prevent the air in the region having a high dynamic pressure from directly flowing into the air intake, so that the flow rate of the air flowing into the air intake can be effectively made uniform throughout.

  In the present invention, the fuel supply unit is disposed on the upstream side of the air intake port, has an annular main fuel supply portion concentric with the air intake port, and the cover portion surrounds an outer periphery of the main fuel supply portion. It can also be set as the structure which consists of a ring body. As a result, after the air in the region having a high dynamic pressure is once returned to the static pressure by the ring body, the air is drawn into the air intake port by the differential pressure between the pressure of the air and the pressure in the combustion chamber. The air can be introduced at a uniform flow rate throughout the air intake.

  In the present invention, the ring body is preferably supported by the fuel supply unit. Thereby, since the ring body is supported by the existing fuel supply unit, a dedicated support member is not required separately.

  In this invention, it is preferable that the outer diameter of the outer periphery of the said ring body is larger than the outer diameter of the air intake port of the said fuel injection unit. Thereby, the ring body can block the air intake and effectively return the air in the high dynamic pressure region to the static pressure.

  According to the combustion apparatus for a gas turbine engine of the present invention, the cover portion rectifies the compressed air so that the compressed air flows at a uniform flow rate throughout the air intake port. Since the premixed gas having a uniform mixture concentration is generated, the flame temperature in the combustion chamber can be made uniform, the amount of NOx generated can be suppressed, and a sufficient lifetime of the liner constituting the combustion chamber can be ensured. In addition, a uniform turbine temperature can be secured as the outlet temperature distribution of the combustor is made uniform, and a good backflow region is stably formed in the combustion chamber, so that stable combustion, good ignition and high combustion are achieved. Efficiency can be secured.

  Hereinafter, preferred embodiments of the present invention will be described with reference to the drawings. FIG. 1 shows a head of a combustor 1 constituting a combustion apparatus for a gas turbine engine according to a first embodiment of the present invention. The combustor 1 combusts an air-fuel mixture generated by mixing fuel with compressed air supplied from a compressor (not shown) of a gas turbine engine, and sends high-temperature and high-pressure combustion gas generated by the combustion to the turbine. The turbine is driven.

  The combustor 1 is an annular type, an annular inner casing 8 is concentrically disposed inside an annular outer casing 7, and has a cyclic internal space that is concentric with a gas turbine axis (rotation axis). A housing 6 is configured. In the annular inner space of the combustion device housing 6, a combustion cylinder 9 in which an annular inner liner 11 is concentrically disposed inside the annular outer liner 10 is disposed concentrically with the combustion device housing 6. The combustion cylinder 9 has an annular combustion chamber 12 formed therein, and a plurality (14 in this embodiment) of fuel injection units 2 that inject fuel into the combustion chamber 12 on the top wall 9a of the combustion cylinder 9. Are arranged at equal intervals on a single circle concentric with the combustion cylinder 9. Each fuel injection unit 2 includes a fuel injection unit (pilot fuel injection nozzle) 3 and a premixed gas supply unit (main fuel injection unit) concentrically provided with the fuel injection unit 3 so as to surround the outer periphery of the fuel injection unit 3. Nozzle) 4. Details of the fuel injection unit 3 and the premixed gas supply unit 4 will be described later.

  Two spark plugs 13 for penetrating through the outer casing 7 and the outer liner 10 are provided so as to face the radial direction of the combustion cylinder 9 and have their tips opposed to the fuel injection unit 2. Therefore, in the combustor 1, the combustible air-fuel mixture from the two fuel injection units 2 facing the two spark plugs 13 is first ignited, and the flame caused by this combustion is combusted from the adjacent fuel injection units 2. Then, it propagates while moving one after another, and the combustible air-fuel mixture from all the fuel injection units 2 is ignited.

  FIG. 2 is an enlarged longitudinal sectional view taken along line II-II in FIG. Compressed air CA fed from the compressor is introduced into the annular internal space of the combustion device housing 6 through the internal passage of the annular diffuser 14 from the air inlet 14a at the downstream end thereof. The compressed air CA is supplied to the fuel injection unit 2 through an opening 27 a provided in the cowl 27 that covers the upstream end of the combustion cylinder 9, and is guided to the outside of the combustion cylinder 9 by the cowl 27. Nine outer liners 10 and inner liners 11 are supplied into the combustion chamber 12 through a plurality of cooling air inlets 17.

  The fuel piping unit 18 includes a first fuel supply system F1 that supplies fuel for diffusion combustion to the fuel injection unit 3 and a second fuel that supplies fuel for lean premixed combustion to the premixed gas supply unit 4. A supply system F <b> 2 is provided and is supported by the outer casing 7. A fuel supply unit 20 connected to the fuel pipe unit 18 supplies the fuel F from the fuel pipe unit 18 to the fuel injection unit 2. The fuel supply unit 20 is disposed so as to penetrate the opening 27a of the cowl 27, and details thereof will be described later. The fuel injection unit 2 is supported by the outer liner 10 via a flange 5A provided on the outer periphery thereof and a support 5B provided on the outer liner 10, and the outer liner 10 is supported on the outer casing 7 by a liner fixing pin P. Yes. A turbine first stage nozzle TN is connected to the downstream end of the combustion cylinder 9.

  The fuel injection unit 3 is provided at the center of the fuel injection unit 2. The fuel injection unit 3 includes an inner and outer double annular swirler 33 and a diffusion nozzle 32. The fuel injection unit 3 is supplied from the first fuel supply system F1 of the fuel pipe unit 18 and supplies the pilot fuel to the fuel supply unit 20. The fuel F injected from the fuel injection hole of the part 31 is atomized by the compressed air CA that has passed through the swirler 33 and then sprayed into the combustion chamber 12 through the diffusion nozzle 32 to form the diffusion combustion region 50. . The annular premixed gas supply unit 4 is provided so as to surround the outer periphery of the fuel injection unit 3. The premixed gas supply unit 4 includes a premixing passage 42 and an inner / outer double annular swirler 43, and is fed from the second fuel supply system F 2 of the fuel pipe unit 18 to be annular in the fuel supply unit 20. The fuel F injected into the premixing passage 42 from the fuel injection holes arranged at equal intervals in the circumferential direction in the main fuel supply unit 41 is mixed with the compressed air CA that has passed through the swirler 43 to generate premixed gas, This is injected into the combustion chamber 12 to form a premixed combustion region 51.

  The fuel injection unit 3 and the premixed gas supply unit 4 take in the compressed air CA using the inner and outer double swirlers 33 and 43 as annular air intakes. The fuel supply unit 20 has a configuration in which a pilot fuel supply unit 31 and a main fuel supply unit 41 are connected to a unit base body 19. The fuel supply unit 20 has a predetermined number of fuel injection units 3 with the pilot fuel supply unit 31 fitted into the annular swirler 33 and the main fuel supply unit 41 fitted into the annular swirler 43. They are fastened together by fitting pins (not shown).

  The fuel F is supplied to the fuel injection unit 3 from the first fuel supply system F1 in the entire load region. The premixed gas supply unit 4 includes a second fuel at a high load of, for example, 70% or more with respect to the total load, and at a high load and a low load, for example, at a medium load of 40 to 70% of the full load. Fuel F is supplied from the supply system F2. The premixed gas supply unit 4 supplies only the compressed air CA to the combustion chamber 12 through the swirler 43 because the fuel F is not supplied at a low load of 40% or less with respect to the total load.

  FIG. 3 is a perspective view showing the relative relationship among the cowl 27, the fuel supply unit 20, and the fuel injection unit 3, which are the main parts of the combustor 1. An annular main fuel supply unit 41 concentric with the swirler 43 is inserted into the swirler 43 from the upstream side (front side in the figure) and is located in the center of the main fuel supply unit 41. 31 is inserted into the inner and outer double swirlers 33 of the fuel injection unit 3 in FIG. 2 from the upstream side thereof and connected to the fuel injection unit 2. The inlet 43 a of the swirler 43 forms the air intake of the premixed gas supply unit 4, the inlet 33 a of the swirler 33 forms the air intake of the fuel injection unit 3, and the main fuel supply unit 41 of the fuel supply unit 20. The main part except for is located on the upstream side of these air intake ports 43a and 33a.

  The cowl 27 is disposed on the upstream side of the swirlers 33 and 43 that are the air intake ports of the fuel injection unit 3 and the premixed gas supply unit 4 in the fuel supply unit 2. An opening 27 a for introducing the compressed air CA into the fuel injection unit 2 is formed in the cowl 27 in a long hole shape.

  FIG. 4 is a view taken in the direction of arrow A in FIG. 3, and the openings 27a of the cowl 27 are linearly parallel to each other and extend in the radial direction R at both sides in the gas turbine circumferential direction Q. When viewed from the axial direction of the supply unit 4, it overlaps with the swirler 43 of the premixed gas supply unit 4. Both side portions in the gas turbine radial direction R do not overlap the swirler 43 when viewed from the axial direction, and are largely separated in the radial direction R so that the upper and lower portions of the swirler 43 are exposed. Thereby, the opening 27a has a long hole shape long in the radial direction R. A gap C1 between the main fuel supply unit 41 of the fuel supply unit 20 in the circumferential direction Q of the gas turbine and a hole edge of the opening 27a is set to a small dimension that absorbs a manufacturing dimensional tolerance, and the swirler 43 in the radial direction R The gap C2 with the hole edge of the opening 27a is set to about 1 to 3 times the gap C1 so as to absorb the manufacturing dimensional tolerance and the relative displacement difference during operation. The high dynamic pressure region HA having a width W corresponding to the opening flow path height of the air introduction hole 14a of the diffuser 14 of FIG. 2 and annularly distributed in the gas turbine circumferential direction Q in a belt shape is the gas turbine in the opening 27a of FIG. It passes through the central part in the radial direction R.

  The part that enters the high dynamic pressure region HA in the inner and outer double swirler 43 of the premixed gas supply unit 4 is only a part of the inner swirler 43, and the other part is closed by the cover part 27b. . As shown in FIG. 5, the cover portion 27a is separated from the air intake port 43a on the upstream side in the axial direction of the premixed gas supply portion 4, and the air introduction path 61 is provided between the cover portion 27a and the air intake port 43a. Is formed. Accordingly, the compressed air CA in the high dynamic pressure area HA is rectified to a low dynamic pressure substantially equal to that of the compressed air CA other than the high dynamic pressure area HA due to a drop in the flow velocity upon hitting the cover portion 27b, and then the cover portion. The air passes through the opening 27a from the hole edge near 27b and flows into the swirler 43 through the air introduction path 61. On the other hand, the compressed air CA other than the high dynamic pressure region HA flows into the swirler 43 through the opening 27a as it is. That is, the compressed air CA flows into the swirler 43 after being rectified so as to have substantially the same flow velocity throughout the swirler 43. Thereby, the inflow amount of the compressed air CA of the swirler 43 is made uniform in place throughout the swirler 43.

  Note that the entire area of the swirler 33 of the fuel injection unit 3 is included in the high dynamic pressure region HA, and therefore the compressed air CA flows in as it is, so that the non-uniform problem as in the premixed gas supply unit 4 does not occur. .

  Therefore, in the premixed gas supply unit 4, the compressed air CA and the fuel are mixed at a uniform mixing ratio in the entire circumferential direction, and a mixed gas whose mixture concentration, that is, the air-fuel ratio is constant throughout the combustion chamber 12 is mixed. To be supplied. As a result, the flame temperature in the combustion chamber 12 becomes uniform, so that the amount of NOx generated due to the high-temperature flame can be suppressed, and the walls of the liners 10 and 11 constituting the combustion chamber 12 have a temperature distribution. Since hot spots accompanying non-uniformity do not occur, they are not easily damaged, and a sufficient lifetime of the liners 10 and 11 can be ensured. Moreover, since the outlet temperature distribution of the combustor 1 is also made uniform, the first nozzle TN of the turbine is prevented from being burned by a hot spot and generating high thermal stress, thereby ensuring a sufficient life. Furthermore, since the velocity distribution of the air-fuel mixture supplied from the pre-air mixture supply unit 4 is made uniform, a good backflow region can be stably formed in the combustion chamber 12, so that stable combustibility, good ignitability, and high Combustion efficiency can be ensured. Further, the pressure loss caused by temporarily blocking the flow of the compressed air CA in the high dynamic pressure region HA by the cover portion 27b is offset by a large rectifying effect that can equalize the flow velocity of the compressed air flowing into the entire swirler 43. It has been confirmed by experiments that these effects can be obtained.

  In addition, as shown by a two-dot chain line U in FIG. Therefore, in this combustor 1, the cover portion 27b can be formed integrally with the cowl 27 only by forming the opening 27a whose hole shape is changed to a long hole in the existing cowl 27, and there is no need to provide a dedicated cover portion separately. Therefore, there is an advantage that the various effects described above can be obtained with a simple configuration in which an increase in the number of parts is suppressed.

  FIG. 6 is a perspective view showing a main part of a combustor according to the second embodiment of the present invention. In this combustor, an existing cowl 29 having a circular opening 29a is used, and a ring body 34 surrounding the outer periphery of the main fuel supply part 41 of the fuel supply unit 20 is provided as a cover part. The ring body 34 is fixed to the outer peripheral surface of the main fuel supply portion 41 by welding or brazing in a state where the outer peripheral surface of the main fuel supply portion 41 is fitted in the mounting hole 34a at the center thereof.

  FIG. 7 shows a partially cutaway side view of FIG. 6, wherein the ring body 34 has an outer diameter larger than the outer diameter D of the swirler 43 that forms the air inlet 43a outside the fuel injection unit 2, and It consists of the board | plate material formed in the bowl-shaped curved surface shape along the front-end part of the cowl 29. FIG. The ring body 34 is provided on the upstream side of the cowl 29 in such a relative arrangement that the gap C is substantially constant with respect to the cowl 29, and air is introduced into the swirler 43 between the ring body 34 and the swirler 43. A path 61A is formed. The size of the gap C is approximately the same as in the first embodiment.

  In the combustor provided with the ring body 34, since the ring body 34 covers the entire outer portion of the outer peripheral surface of the main fuel supply unit 41 in the fuel injection unit 2, the ring body 34 faces the swirler 43 of the premixed gas supply unit 4. The compressed air CA that has flowed in this manner is once blocked by the ring body 34, and then flows from the outer peripheral edge of the ring body 34 to the air introduction path 61 </ b> A between the ring body 34 and the cowl 29. It flows into the cowl 29 through 29a. The compressed air CA that has entered the cowl 29 is once taken back into the swirler 43 by a differential pressure between the pressure in the cowl 29 and the combustion chamber 12 after a part of the dynamic pressure is returned to static pressure. Therefore, since the compressed air CA flows at almost the same flow rate throughout the swirler 43, the inflow amount of the compressed air CA of the swirler 43 is made uniform locally throughout the swirler 43, as described in the first embodiment. Similar effects can be obtained. In addition, in this embodiment, the existing cowl 29 is used as it is, and it is only necessary to newly provide a ring body 34 with a simple shape.

  FIG. 8 is a perspective view showing a main part of a combustor according to the third embodiment of the present invention. In this combustor, except for the cowl, a ring body 37 formed with a circular attachment hole 37a into which the outer peripheral surface of the main fuel supply part 41 can be fitted is provided as a cover part.

  FIG. 9 is a partially cutaway side view of FIG. The ring body 37 has a simple spherical shape and has an outer diameter larger than the outer diameter D of the swirler 43 that is an air intake port outside the fuel injection unit 2 when viewed from the axial direction of the premixed gas supply unit 4. An air introduction path 61 </ b> B is formed between the circular outer periphery and the swirler 43. Accordingly, the ring body 37 can function in substantially the same manner as in the second embodiment to obtain the same effect, and the ring body 34 having a complicated spherical surface along the cowl 27 of the second embodiment. Unlike the case, since it has a simple spherical surface, there is an advantage that it can be easily manufactured. In addition, since the configuration can be simplified by removing the cowl, the cost can be reduced.

1 is a schematic front view showing a combustion apparatus for a gas turbine engine according to a first embodiment of the present invention. It is an expanded sectional view along the II-II line of FIG. It is a perspective view which shows the principal part structure of 1st Embodiment. FIG. 4 is a view in the direction of arrow A in FIG. 3. It is a longitudinal cross-sectional view which expands and shows the principal part of FIG. It is a perspective view which shows the principal part in the combustor which concerns on 2nd Embodiment of this invention. FIG. 7 is a partially cutaway side view of FIG. 6. It is a perspective view which shows the principal part in the combustor which concerns on 3rd Embodiment of this invention. FIG. 9 is a side view of FIG. 8 partially cut away.

Explanation of symbols

2 Fuel injection unit 3 Fuel injection part 4 Premixed gas supply part 9 Combustion cylinder 12 Combustion chamber 20 Fuel supply unit 27 Cowl 27a Opening 27b Cover part 31 Pilot fuel supply part 33, 43 Swirler 33a, 43a Air intake 34, 37 Ring Body (cover part)
41 Main fuel supply unit 50 Diffusion combustion region 51 Premixed gas combustion region 61, 61A, 61B Air introduction path F Fuel CA Compressed air

Claims (7)

An annular combustion cylinder forming a combustion chamber;
A plurality of fuel injection units having a premixed gas supply unit for supplying a premixed gas of fuel and air so as to form a premixed gas combustion region in the combustion chamber;
A fuel supply unit for supplying fuel to the premixed gas supply unit;
An annular air inlet for introducing compressed air from a compressor to the upstream side of the fuel injection unit;
A cover portion positioned upstream in the axial direction with respect to the annular air intake port in the premixed gas supply portion, and the cover portion is arranged spaced apart from the air intake port in the axial direction upstream And a combustion apparatus for a gas turbine engine, wherein an air introduction path is formed between the air intake and at least a portion of the air intake as viewed in the axial direction.   2. The fuel injection unit according to claim 1, further comprising a fuel injection unit that sprays fuel so as to form a diffusion combustion region in the combustion chamber, the fuel injection unit being the center of the annular premixed gas supply unit The main part of the fuel supply unit is located upstream of the air intake, and is located at the center of the annular main fuel supply part concentric with the air intake. A combustion apparatus for a gas turbine engine, comprising: a pilot fuel supply unit that supplies pilot fuel to the fuel injection unit.   3. The cowl according to claim 1, further comprising a cowl that covers an upstream end portion of the combustion cylinder and guides compressed air upstream of the fuel injection unit to the outside of the combustion cylinder, and the cowl is supplied to the fuel injection unit. A combustion apparatus for a gas turbine engine having an opening through which the cover is integrally formed with the cowl.   4. The fuel supply unit according to claim 3, wherein the fuel supply unit is disposed on the upstream side of the air intake and includes the annular main fuel supply portion concentric with the air intake, and the cover portion has an opening in the cowl. The combustion apparatus of the gas turbine engine currently formed in the both sides which oppose a gas turbine circumferential direction.   3. The fuel supply unit according to claim 1, wherein the fuel supply unit is disposed on an upstream side of the air intake, has an annular main fuel supply part concentric with the air intake, and the cover part of the main fuel supply part A combustion apparatus for a gas turbine engine comprising a ring body surrounding an outer periphery.   6. The combustion apparatus for a gas turbine engine according to claim 5, wherein the ring body is supported by the fuel supply unit.   The combustion apparatus for a gas turbine engine according to claim 5 or 6, wherein an outer diameter of an outer peripheral edge of the ring body is larger than an outer diameter of an air intake port of the fuel injection unit.

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