JP7301656B2 - fuel nozzles and gas turbine engines - Google Patents

Description

The present disclosure relates to fuel nozzles and gas turbine engines.

Conventionally, among fuel nozzles used in gas turbines that use liquid fuel, pressure spray fuel nozzles or combinations of pressure spray fuel nozzles and air blast fuel nozzles are known (see, for example, Patent Document 1). ). A pressure atomizing fuel nozzle atomizes a liquid fuel through an injection hole. The air blast type fuel nozzle spreads the liquid fuel in the form of a film and atomizes the liquid film by the shearing action of air currents flowing in contact with the surface of the liquid film.

A fuel nozzle for a gas turbine described in FIG. 2 of Patent Document 1 has a pressure spray type fuel nozzle (pressure swirl nozzle) arranged coaxially inside an air blast type nozzle (airflow atomization nozzle). Patent Literature 1 discloses that the inner diameter of a drift cylinder disposed between an air atomization nozzle and a pressure swirl nozzle is once minimized downstream of the flow path, and then expanded toward the tip. According to Patent Document 1, since the flow does not separate on the tip surface of the pressure swirl nozzle and a backflow region is not formed, the sprayed fuel flows back and adheres to the tip surface of the pressure swirl nozzle and deposits as carbon. can solve the problem.

JP 2004-360944 A

However, in the fuel nozzle disclosed in Patent Literature 1, when fuel adheres to the wall surface where the inner diameter of the non-uniform flow cylinder increases and deposits as carbon, the fuel injection is hindered and the combustion efficiency increases when the combustor is started. It becomes difficult. Therefore, it is necessary to periodically perform a cleaning operation to remove the deposited carbon. In particular, when the wall surface of the non-uniform flow cylinder whose inner diameter increases is too steep, the wall surface cannot be covered by the airflow flowing through the non-uniform flow cylinder, and the problem of carbon deposition becomes significant.

The present disclosure has been made in view of such circumstances, and the guide section guides the combustion air to the opening including the injection area of the pressure spray type fuel nozzle so that carbon is deposited in the vicinity of the injection hole. It is an object of the present invention to provide a fuel nozzle and a gas turbine engine equipped with the fuel nozzle, which can suppress this and can suppress the deposition of carbon on the surface of the guide portion.

In order to solve the above problems, the fuel nozzle according to one aspect of the present disclosure is a pressure injection type fuel nozzle that is arranged along the axis and injects the first liquid fuel from the injection hole toward the combustion chamber to atomize it. A first nozzle portion and an air flow path formed in a cylindrical shape along the axis and disposed on the outer peripheral side of the first nozzle portion for circulating combustion air are formed between the first nozzle portion and the first nozzle portion. a swirler arranged in the air flow path and imparting a swirling force to swirl the combustion air flowing through the air flow path around the axis; and a guide portion that guides the first nozzle portion to an opening that surrounds an injection region in which the first liquid fuel is injected; a second nozzle portion for circulating a mixture of the atomized second liquid fuel and the combustion air between the cylinder portion and the guide portion, the guide portion being guided to the injection area by the guide portion; an air flow mechanism for directing part of the combustion air to be used for combustion directly to the combustion chamber without passing through the opening.

According to the present disclosure, the guide portion guides the combustion air to the opening including the injection region of the pressure spray type fuel nozzle to suppress the deposition of carbon in the vicinity of the injection hole, and the carbon is deposited on the surface of the guide portion. It is possible to provide a fuel nozzle and a gas turbine engine having the same that can suppress the deposition of .

1 is a vertical cross-sectional view of a fuel nozzle according to a first embodiment of the present disclosure; FIG. FIG. 2 is a vertical cross-sectional view showing a cylinder portion, a guide portion, and a flange portion shown in FIG. 1; 2 is a cross section of the fuel nozzle shown in FIG. 1 taken along the line AA. 2 is a partial cross-sectional view of the fuel nozzle shown in FIG. 1; FIG. FIG. 3 is a front view of the fuel nozzle shown in FIG. 2 as viewed from the combustion chamber side along the axis; FIG. 5 is a front view of a fuel nozzle according to a second embodiment of the present disclosure, viewed along the axis from the combustion chamber side; FIG. 5 is a vertical cross-sectional view of a fuel nozzle according to a third embodiment of the present disclosure; FIG. 8 is a cross-sectional view of the fuel nozzle shown in FIG. 7 taken along the line BB. It is a cross-sectional view showing a modification of the swirler.

[First embodiment]
A fuel nozzle 100 according to a first embodiment of the present disclosure will be described below with reference to the drawings. FIG. 1 is a vertical cross-sectional view showing a fuel nozzle 100 according to the first embodiment of the present disclosure. FIG. 2 is a longitudinal sectional view showing the tubular portion 20, the guide portion 30, and the flange portion (enlarged diameter portion) 40 shown in FIG. FIG. 3 is a cross section of the fuel nozzle 100 shown in FIG. 1 taken along line AA. FIG. 4 is a partial cross-sectional view of fuel nozzle 100 shown in FIG. 5 is a front view of the fuel nozzle 100 shown in FIG. 2 as viewed from the combustion chamber CC side along the axis X. FIG.

The fuel nozzle 100 of the present embodiment is provided, for example, in a combustor of a gas turbine engine used in a small aircraft or the like. A gas turbine engine having a combustor equipped with the fuel nozzle 100 of this embodiment is driven by a turbine driven by combustion gas generated in the combustor by burning liquid fuel, and by the driving force of the turbine. It has a drive shaft. The driving force transmitted from the turbine to the drive shaft is used as power to rotate a propeller or the like connected to the drive shaft.

As shown in FIG. 1, the fuel nozzle 100 of the present embodiment includes a pressure injection type first nozzle portion 10, a cylinder portion 20, a guide portion 30, a flange portion (diameter enlarged portion) 40, and a swirler 50. and an air blast type second nozzle part 60 .

The first nozzle part 10 is arranged along the axis X and injects a first liquid fuel supplied from a first liquid fuel supply source (not shown) from an injection hole 11 toward the combustion chamber CC to atomize it. It is a pressure injection type fuel nozzle that allows The first nozzle part 10 atomizes the first liquid fuel when injecting the high-pressure first liquid fuel from the injection hole 11 into the combustion chamber CC, and atomizes the first liquid fuel toward a radial injection area JA centered on the axis line X. The first liquid fuel is injected.

The tubular portion 20 is a tubular body that is formed in a tubular shape along the axis X and is coaxially arranged on the outer peripheral side of the first nozzle portion 10 . The tubular portion 20 forms an air flow path AP for circulating the combustion air CA between itself and the first nozzle portion 10 . The air flow path AP is a flow path that is annularly formed around the axis X. As shown in FIG. Combustion air CA is supplied to the air flow path AP from a combustion air supply source (not shown).

The guide portion 30 is a member that guides the combustion air CA that has passed through the swirler 50, which will be described later, to the opening portion 31 that surrounds the injection area JA where the first nozzle portion 10 injects the first liquid fuel. As shown in FIG. 2, the guide portion 30 has a convex outer peripheral surface 30b whose outer diameter OD1 gradually decreases toward the opening portion 31 along the axis X. As shown in FIG.

The guide part 30 guides the air flow of the combustion air CA having a swirling component around the axis X after passing through the swirler 50 from the outer peripheral side to the inner peripheral side in the radial direction perpendicular to the axis X, thereby guiding the combustion air CA. It is led to the combustion chamber CC from the opening 31 together with the atomized first liquid fuel. Since the combustion air CA having a swirling component converges radially inward and then passes through the opening 31, the first liquid fuel sprayed into the combustion chamber CC flows from the opening 31 to the first nozzle 10. is prevented from flowing back to the tip of the Thereby, deposition of carbon in the vicinity of the injection hole 11 is suppressed.

As shown in FIG. 2, the flange portion 40 is a member that connects the end portion of the combustion chamber CC of the cylinder portion 20 and the end portion of the guide portion 30 on the cylinder portion 20 side. The flange portion 40 is integrally formed with the tubular portion 20 and the guide portion 30 from a single material. The flange portion 40 has a shape in which the outer diameter OD2 gradually expands toward the combustion chamber CC so as to guide the mixture MA of the second liquid fuel and the combustion air guided from the second nozzle portion 60 in a direction away from the axis X. have As shown in FIG. 1, the air-fuel mixture MA flowing along the axis X in the air-fuel mixture flow path MP of the second nozzle portion 60 along the outer peripheral side of the cylindrical portion 20 moves away from the axis X when passing through the flange portion 40. be guided in the direction

The swirler 50 is a device that is arranged in the air flow path AP and imparts a swirling force that causes the combustion air CA flowing through the air flow path AP to swirl around the axis X. As shown in FIG. The swirler 50 is annularly arranged in the circumferential direction around the axis X. As shown in FIG. As shown in FIG. 3, the swirler 50 includes a plurality of swirl vanes 51 that are circumferentially arranged around the axis X at intervals. As shown in FIG. 3 , the swirl vane 51 imparts a swirl force to the combustion air CA so that the fuel nozzle 100 swirls clockwise around the axis X when viewed from the combustion chamber CC side along the axis X.

FIG. 4 is a partial cross-sectional view of the fuel nozzle 100 shown in FIG. 1, and shows a perspective view of a state in which the first nozzle portion 10, the cylinder portion 20, the guide portion 30, and the flange portion 40 are partially cut. . As shown in FIG. 4, the fuel nozzle 100 has a structure in which a plurality of swirl vanes 51 are arranged at intervals along the circumferential direction between the first nozzle portion 10 and the tubular portion 20 .

The second nozzle portion 60 is a device formed in a tubular shape along the axis X and arranged on the outer peripheral side of the tubular portion 20 . The second nozzle part 60 spreads the second liquid fuel supplied from the second liquid fuel supply source (not shown) into a film, and spreads the liquid film by the shearing action of the combustion air flowing in contact with the surface of the liquid film. It is atomized. The second nozzle part 60 circulates the air-fuel mixture MA obtained by mixing the atomized second liquid fuel and the combustion air in the air-fuel mixture flow path MP formed between the second nozzle part 60 and the cylindrical part 20 .

Next, the through hole (air circulation mechanism) 32 and the through hole (air circulation mechanism) 33 provided in the guide portion 30 will be described. As described above, the guide portion 30 guides the airflow of the combustion air CA from the outer peripheral side to the inner peripheral side in the radial direction orthogonal to the axis X, and guides the combustion air CA having the swirling component to the radial inner peripheral side. By passing through the opening 31 after being converged, the deposition of carbon in the vicinity of the injection hole 11 can be suppressed.

While the guide portion 30 has the above advantages, there is a possibility that fuel or the like will adhere to the surface of the guide portion 30 (the surface facing the combustion chamber CC) and carbon will accumulate. Therefore, in the present embodiment, by providing the through holes 32 and 33 in the guide portion 30, the combustion air CA is blown out toward the carbon deposited on the surface of the guide portion 30, thereby of carbon deposits are prevented.

As shown in FIGS. 2 and 5, the guide portion 30 directs part of the combustion air CA guided to the injection area JA by the guide portion 30 directly to the combustion chamber CC without passing through the opening 31. It has through holes 32 and 33 for guiding. The through holes 32 and 33 are formed in a plurality of locations of a structure made of a metallic material that does not allow the combustion air CA to pass therethrough so that the combustion air CA can be directed directly to the combustion chamber CC without passing through the openings 31. It is a mechanism that leads to

As shown in FIG. 4, the through hole 32 is a hole that allows an inlet 32a formed on the inner peripheral surface 30a of the guide portion 30 and an outlet 32b formed on the outer peripheral surface 30b of the guide portion 30 to communicate with each other. . Similarly, the through hole 33 is a hole that allows an inlet port 33a formed in the inner peripheral surface 30a of the guide portion 30 and an outlet port 33b formed in the outer peripheral surface 30b of the guide portion 30 to communicate with each other.

As shown in FIG. 5 , on the outer peripheral surface 30b of the guide portion 30, a plurality of circles centered on the axis X and having a radius R1 are arranged at intervals along the circumferential direction around the axis X. A discharge port 32b is formed. In the inner peripheral surface 30a of the guide portion 30, a plurality of inlets 32a are formed with a circle having a radius R2 centered on the axis X and spaced apart along the circumferential direction around the axis X. ing.

Since the radius R1 is larger than the radius R2, the combustion air CA that has flowed into the through hole 32 from the inlet 32a has a velocity component radially outward about the axis X and is discharged from the outlet 32b. It is discharged to the combustion chamber CC. Further, the discharge port 32b is located downstream of the inlet port 32a in the clockwise direction in the circumferential direction. Therefore, when the guide portion 30 is viewed from the combustion chamber CC side along the axis X, the combustion air CA flowing into the through hole 32 from the inlet 32a has a clockwise velocity component about the axis X. In this state, the fuel is discharged from the discharge port 32b into the combustion chamber CC. Thus, the through hole 32 imparts a swirling force to swirl about the axis X to the combustion air CA led to the combustion chamber CC.

As shown in FIG. 5 , on the outer peripheral surface 30b of the guide portion 30, a plurality of circles centered on the axis X and having a radius R3 are arranged at intervals along the circumferential direction around the axis X. A discharge port 33b is formed. In the inner peripheral surface 30a of the guide portion 30, a plurality of inlets 33a are formed with a circle centered on the axis X and having a radius R4, and are spaced apart along the circumferential direction around the axis X. ing.

Since the radius R3 is larger than the radius R4, the combustion air CA that has flowed into the through hole 33 from the inlet 33a has a velocity component radially outward about the axis X and is discharged from the outlet 33b. It is discharged to the combustion chamber CC. Further, the discharge port 33b is located downstream of the inlet port 33a in the clockwise direction in the circumferential direction. Therefore, when the guide portion 30 is viewed from the combustion chamber CC side along the axis X, the combustion air CA flowing into the through hole 33 from the inlet 33a has a clockwise velocity component about the axis X. In this state, the fuel is discharged from the discharge port 33b into the combustion chamber CC. Thus, the through hole 33 imparts a swirling force to swirl about the axis X to the combustion air CA led to the combustion chamber CC.

As shown in FIG. 5, the guide portion 30 directs the combustion air CA to which the swirl force about the axis X is imparted to the combustion chamber CC through a plurality of discharge ports 32b and a plurality of discharge ports 33b formed in the outer peripheral surface 30b. lead to When the guide portion 30 is viewed from the combustion chamber CC side along the axis X, the combustion air CA discharged from the plurality of discharge ports 32b and the plurality of discharge ports 33b is discharged from the plurality of discharge ports 32b and the plurality of discharge ports 33b. also flows along the outer peripheral surface 30b of the guide portion 30 on the outer peripheral side. Therefore, carbon is prevented from accumulating on the outer peripheral surface 30b of the guide portion 30 on the outer peripheral side of the plurality of discharge ports 32b and the plurality of discharge ports 33b.

As shown in FIG. 5, when the guide portion 30 is viewed from the combustion chamber CC side along the axis X, the plurality of discharge ports 32b and the plurality of discharge ports 32b are located in the region on the inner peripheral side of the plurality of discharge ports 32b and 33b. and the combustion air CA discharged from the plurality of discharge ports 33b is not guided. However, the carbon is prevented from accumulating on the region on the inner peripheral side of the plurality of discharge ports 32b and the plurality of discharge ports 33b. This is because the combustion air CA jetted from the openings 31 and imparted with a swirling force flows through the regions on the inner peripheral side of the plurality of discharge ports 32b and the plurality of discharge ports 33b.

The operation and effects of the fuel nozzle 100 according to the present embodiment described above will be described.
According to the fuel nozzle 100 of the present embodiment, the combustion air CA passed through the swirler 50 by the guide portion 30 and imparted with swirl force reaches the injection area JA where the first nozzle portion 10 injects the first liquid fuel. and is ejected from the opening 31 into the combustion chamber CC. The combustion air CA converged in the opening portion 31 with the swirl force prevents the first liquid fuel injected from the first nozzle portion 10 from flowing back and adhering to the vicinity of the injection hole 11. The deposition of carbon in the vicinity of 11 can be suppressed.

Further, according to the fuel nozzle 100 according to the present embodiment, the guide part 30 directs part of the combustion air CA guided to the injection area JA directly to the combustion chamber CC without passing through the opening part 31. Since the guiding through holes 32 and 33 are provided, the combustion air CA guided from the through holes 32 and 33 flows along the surface (outer peripheral surface 30b) of the guide portion 30 on the side of the combustion chamber CC. Thereby, it is possible to suppress the deposition of carbon on the surface of the guide portion 30 .

In the fuel nozzle 100 of this embodiment, the guide portion 30 has a convex outer peripheral surface 30b whose outer diameter OD1 gradually decreases toward the opening portion 31 along the axis X. As shown in FIG. The guide portion 30 having the convex outer peripheral surface 30b is in a state where the combustion air CA ejected from the opening 31 does not flow as the distance from the opening 31 increases. According to the fuel nozzle 100 of the present embodiment, since the guide portion 30 has the through holes 32 and 33, even if the guide portion 30 has the convex outer peripheral surface 30b, carbon deposition on the surface of the guide portion 30 can be prevented. can be reliably suppressed.

In the fuel nozzle 100 of the present embodiment, the through holes 32 and 33 give a swirling force to swirl about the axis X to the combustion air CA guided to the combustion chamber CC.
Since the combustion air CA ejected from the through holes 32 and 33 is imparted with a swirling force to swirl around the axis X, the carbon adhering to the outer peripheral surface of the guide portion 30 on the side of the combustion chamber CC can be more reliably removed. can.

The fuel nozzle 100 according to the present embodiment connects the end portion of the cylindrical portion 20 on the side of the combustion chamber CC and the end portion of the guide portion 30 on the side of the cylindrical portion 20, and guides from the second nozzle portion 60 to the combustion chamber CC. A flange portion 40 having an outer diameter OD2 gradually increasing toward the combustion chamber CC is provided so as to guide the air-fuel mixture to be drawn away from the axis X.

According to the fuel nozzle 100 according to the present embodiment, the air-fuel mixture MA guided from the second nozzle portion 60 is guided by the flange portion 40 in a direction away from the axis X, and accordingly the airflow flows downstream of the flange portion 40. A stagnation region in which is suppressed is formed. In the stagnation region, the possibility of carbon deposition due to adhesion of fuel or the like increases. According to the fuel nozzle 100 according to the present embodiment, since the guide portion 30 has the through holes 32 and 33, even if the guide portion 30 has the flange portion 40, carbon is reliably prevented from being deposited on the surface of the guide portion 30. can be suppressed.

According to the fuel nozzle 100 according to the present embodiment, the plurality of swirl vanes 51 arranged at intervals along the circumferential direction around the axis X causes the passing combustion air CA to swirl around the axis X. can be given.

[Second embodiment]
Next, a fuel nozzle 100A according to a second embodiment of the present disclosure will be described. This embodiment is a modified example of the first embodiment, and is assumed to be the same as the first embodiment except for the case where it will be particularly described below, and the description below will be omitted.

The fuel nozzle 100 of the first embodiment directly guides the combustion air CA for removing carbon deposited on the combustion chamber CC side surface of the guide portion 30 to the combustion chamber CC without passing through the opening 31. A plurality of through holes 32 and 33 formed in the guide portion 30 are employed as the circulation mechanism. In contrast, the fuel nozzle 100A of the present embodiment employs a porous structure in which air circulation holes are uniformly formed as a structure constituting the air circulation mechanism of the guide portion 30A.

FIG. 6 is a front view of the fuel nozzle 100A according to the present embodiment viewed along the axis X from the combustion chamber CC side. The guide part 30A of the present embodiment directly guides part of the combustion air CA guided to the injection area JA to the combustion chamber CC in the area PA having a radius R5 or more and a radius R6 or less from the axis X. It employs a porous structure in which the air flow holes 34 are uniformly formed.

A region PA of the guide portion 30 shown in FIG. 6 is formed of a porous structure in which air circulation holes 34 are uniformly formed. The air circulation hole 34 formed in the area PA of the guide portion 30A is swirled about the axis X in the combustion air CA guided to the combustion chamber CC, similarly to the through holes 32 and 33 of the first embodiment. give power.

As shown in FIG. 6, the guide portion 30A guides the combustion air CA to which a swirling force around the axis X is applied to the combustion chamber CC through a plurality of air circulation holes 34 formed in the outer peripheral surface 30b. When the guide portion 30A is viewed from the combustion chamber CC side along the axis X, the combustion air CA discharged from the plurality of air circulation holes 34 is discharged from the outer peripheral surface of the guide portion 30 on the outer peripheral side of the plurality of air circulation holes 34. 30b. Therefore, deposition of carbon on the outer peripheral surface 30b of the guide portion 30 on the outer peripheral side of the plurality of air circulation holes 34 is prevented.

As shown in FIG. 6, when the guide portion 30A is viewed from the combustion chamber CC side along the axis X, the area on the inner peripheral side of the area PA includes combustion air CA discharged from the plurality of air circulation holes 34. is not guided. However, deposition of carbon on the area on the inner peripheral side of the area PA is prevented. This is because the combustion air CA jetted from the opening 31 and imparted with a swirling force flows through the area on the inner peripheral side of the area PA.

In the above description, the porous structure in which the air flow holes 34 are uniformly formed is not adopted in the area on the inner peripheral side of the area PA, but other aspects may be adopted. . For example, a porous structure in which the air circulation holes 34 are uniformly formed may be employed for the entire area of the guide portion 30A including the area on the inner peripheral side of the area PA.

According to the fuel nozzle 100A of the present embodiment, by adopting the porous structure in which the air circulation holes 34 are uniformly formed as the guide part 30A, the air is discharged through the air circulation holes 34 formed in the porous structure. , a portion of the combustion air CA can be led directly into the combustion chamber CC.

[Third Embodiment]
Next, a fuel nozzle 100B according to a third embodiment of the present disclosure will be described. The present embodiment is a modified example of the first and second embodiments, and is assumed to be the same as the first embodiment except for the cases where it will be particularly described below, and will not be described below.

The swirler 50 included in the fuel nozzle 100 of the first embodiment includes a plurality of swirl vanes 51 arranged at intervals along the circumferential direction around the axis X. As shown in FIG. On the other hand, the swirler 50A provided in the fuel nozzle 100B of the present embodiment uses an annular member in which a plurality of swirl holes 52 are formed at intervals along the circumferential direction around the axis X. is.

FIG. 7 is a longitudinal sectional view showing a fuel nozzle 100B according to this embodiment. FIG. 8 is a cross-sectional view of the fuel nozzle 100B shown in FIG. 7 taken along line BB. As shown in FIG. 7, the swirler 50A of the present embodiment is an annular member arranged between the outer peripheral surface of the first nozzle portion 10 and the inner peripheral surface of the cylindrical portion 20. As shown in FIG. As shown in FIG. 8, the swirl device 50A is a member that is annularly formed along the circumferential direction around the axis X. As shown in FIG.

As shown in FIG. 8, the swirler 50A is formed with a plurality of swirl holes 52 circumferentially spaced around the axis X. As shown in FIG. As with the swirl vanes 51 of the first embodiment, each swirl hole 52 is arranged around the axis X when the fuel nozzle 100 is viewed from the combustion chamber CC side along the axis X with respect to the passing combustion air CA. Gives a turning force that turns clockwise.

According to the fuel nozzle 100B according to this embodiment, the annular member in which the swirl holes 52 are formed at intervals along the circumferential direction around the axis X causes the combustion air CA passing through the swirl holes 52 to flow around the axis X. It is possible to give a turning force to turn to.

In the above description, the swirler 50A of the fuel nozzle 100B uses an annular member formed with a plurality of swirl holes 52 spaced apart along the circumferential direction around the axis X. However, other modifications are possible.

For example, like the fuel nozzle 100C shown in FIG. 9, the swirler 50B is a porous nozzle having uniformly formed swirling force imparting holes 53 that impart a swirling force to the passing combustion air CA to swirl around the axis X. An annular member made of a structure may also be used. According to the fuel nozzle 100C according to the modification, the swirler 50B made of a porous structure in which the swirling force applying holes 53 are uniformly formed causes the combustion air CA passing through the swirling force applying holes 53 to rotate around the axis X. It is possible to give a turning force to turn to.

[Other embodiments]
In the above description, each part constituting the fuel nozzles 100, 100A, 100B, and 100C may be a combination of independent parts. Moreover, each part constituting the fuel nozzles 100, 100A, 100B, and 100C may be integrally formed of a single material or a plurality of materials (such as metal materials). When integrally forming from a single material or a plurality of materials, additive manufacturing using a 3D printer that laminates metal materials to form a three-dimensional shape may be employed.

The fuel nozzles described in the respective embodiments described above are understood, for example, as follows.
The fuel nozzle (100) according to the present disclosure is a pressure injection type that is arranged along the axis (X) and injects the first liquid fuel from the injection hole (11) toward the combustion chamber (CC) to atomize it. and a first nozzle portion (10) formed in a cylindrical shape along the axis (X) and disposed on the outer peripheral side of the first nozzle portion (10) for combustion between the first nozzle portion (10) A cylindrical portion (20) forming an air flow path (AP) for circulating combustion air, and a combustion air disposed in the air flow path (AP) and flowing through the air flow path (AP) rotate around the axis (X). a swirler (50) that imparts a swirling force to the swirler; ), and a guide portion (30) formed in a tubular shape along the axis (X) and arranged on the outer peripheral side of the tubular portion (20), the tubular portion (20) and a second nozzle portion (60) for circulating a mixture of the second liquid fuel atomized between and the combustion air, wherein the guide portion (30) injects the It has an air flow mechanism (32, 33) that directs part of the combustion air guided to the area (JA) to the combustion chamber (CC) without passing through the opening (31).

According to the fuel nozzle (100) according to the present disclosure, the combustion air (CA) passed through the swirler (50) by the guide portion (30) and given a swirling force is passed through the first nozzle portion (10). It is guided to an opening (31) surrounding an injection area (JA) for injecting the first liquid fuel, and is injected from the opening (31) into the combustion chamber (CC). The first liquid fuel injected from the first nozzle portion (10) flows back and adheres to the vicinity of the injection hole (11) due to the combustion air (CA) converged in the opening portion (31) due to the swirling force. It is possible to suppress the deposition of carbon in the vicinity of the injection hole (11).

Further, according to the fuel nozzle (100) according to the present disclosure, since the guide portion (30) has the air circulation mechanisms (32, 33), the outer peripheral surface of the guide portion (30) on the combustion chamber (CC) side has Combustion air (CA) guided from the air circulation mechanism (32, 33) circulates along it. Thereby, it is possible to suppress the deposition of carbon on the surface of the guide portion.

In the fuel nozzle (100) according to the present disclosure, the guide portion (30) has a convex outer peripheral surface (30a) whose outer diameter (OD1) gradually decreases toward the opening (31) along the axis (X). have
The guide portion (30) having a convex outer peripheral surface (30a) is in a state in which the combustion air (CA) jetted from the opening 31 does not flow as the distance from the opening 31 increases, and carbon deposition due to adhesion of fuel or the like is prevented. more likely. According to the fuel nozzle (100) according to the present disclosure, since the guide part (30) has the air flow mechanism (32, 33), even if the guide part (30) has a convex outer peripheral surface (30a), the guide part ( The deposition of carbon on the surface of 30) can be reliably suppressed.

In the fuel nozzle (100) according to the present disclosure, the air flow mechanism (32, 33) imparts a swirling force to the combustion air (CA) led to the combustion chamber (CC) to swirl around the axis (X).
Since the combustion air (CA) ejected from the air circulation mechanism (32, 33) is given a turning force to turn around the axis (X), the outer peripheral surface of the guide portion (30) on the side of the combustion chamber (CC) Adhering carbon can be removed more reliably.

A fuel nozzle (100) according to the present disclosure connects an end portion of a cylinder portion (20) on the combustion chamber (CC) side and an end portion of a guide portion (30) on the cylinder portion (20) side, and a second An enlarged diameter portion (40) whose outer diameter (OD2) gradually expands toward the combustion chamber (CC) so as to guide the air-fuel mixture led from the nozzle portion (60) to the combustion chamber (CC) in a direction away from the axis (X). ).

According to the fuel nozzle (100) according to the present disclosure, the enlarged diameter portion (40) guides the air-fuel mixture led from the second nozzle portion (60) in a direction away from the axis (X). A stagnation region is formed downstream of (40) in which the air flow is suppressed. In the stagnation region, the possibility of carbon deposition due to adhesion of fuel or the like increases. According to the fuel nozzle (100) according to the present disclosure, since the guide part (30) has the air circulation mechanism (32, 33), even if the guide part (30) has the enlarged diameter part (40), the guide part (30) It is possible to reliably suppress the deposition of carbon on the surface of the

In the fuel nozzle (100) according to the present disclosure, the air circulation mechanisms (32, 33) are through-holes (32, 33) formed at multiple locations in the structure that do not allow passage of combustion air (CA).
According to the fuel nozzle (100) according to the present disclosure, the structure that does not allow the passage of the combustion air (CA) is used to reliably guide the combustion air (CA) to the opening 31, and the penetration formed in the structure Via the holes (32, 33) part of the combustion air (CA) can be led directly into the combustion chamber (CC).

In the fuel nozzle (100A) according to the present disclosure, the air circulation mechanism includes an air circulation hole (34) that directly guides part of the combustion air guided to the injection area (JA) to the combustion chamber (CC). It is a porous structure formed in a similar manner.
According to the fuel nozzle (100A) according to the present disclosure, by adopting the porous structure in which the air flow holes (34) are uniformly formed, the air flow holes (34) formed in the porous structure Via a part of the combustion air (CA) can be led directly to the combustion chamber (CC).

In a fuel nozzle (100) according to the present disclosure, a swirler (50) comprises a plurality of swirl vanes (51) spaced circumferentially about an axis (X).
According to the fuel nozzle (100) of the present disclosure, a plurality of swirl vanes (51) circumferentially spaced about an axis (X) direct the passing combustion air (CA) to the axis. (X) It is possible to apply a turning force to turn around.

In the fuel nozzle (100B) according to the present disclosure, the swirler (50A) is an annular member arranged between the outer peripheral surface of the first nozzle portion (10) and the inner peripheral surface of the cylindrical portion (20), The annular member is formed with a plurality of circumferentially spaced pivot holes (52) about the axis (X).
According to the fuel nozzle (100B) according to the present disclosure, the annular member in which the swirling holes (52) are formed at intervals along the circumferential direction about the axis (X) allows the combustion passing through the swirling holes (52) to be A swirling force can be applied to the air (CA) to swirl around the axis (X).

For example, the gas turbine engine described in each of the embodiments described above is understood as follows.
A gas turbine engine according to the present disclosure includes a combustor having a fuel nozzle (100) that atomizes and combusts a first liquid fuel and a second liquid fuel, and a combustor that combusts the first liquid fuel and the second liquid fuel. a turbine driven by the combustion gases produced thereby.
According to the present disclosure, the guide portion (30) guides the combustion air (CA) to the opening (31) including the injection area (JA) of the pressure atomizing fuel nozzle, and the carbon near the injection hole (11). It is possible to provide a gas turbine engine having a fuel nozzle (100) capable of suppressing the deposition of carbon and the deposition of carbon on the surface of the guide portion (30).

10 First nozzle part 11 Injection hole 20 Cylinder part 30, 30A Guide part 30a Inner peripheral surface 30b Outer peripheral surface 31 Openings 32, 33 Through hole (air circulation mechanism)
34 air flow hole 40 flange portion (diameter enlarged portion)
50, 50A, 50B swirler 51 swirl vane 52 swirl hole 53 swirl force imparting hole 60 second nozzle part 100, 100A, 100B, 100C fuel nozzle AP air flow path CA combustion air CC combustion chamber JA injection area MA mixture MP Air-fuel mixture flow path OD1, OD2 Outer diameter PA Area X Axis

Claims (9)

a pressure-injection type first nozzle portion that is arranged along the axis and injects the first liquid fuel from the injection hole toward the combustion chamber to atomize it;
a cylindrical portion that is formed in a cylindrical shape along the axis and is disposed on the outer peripheral side of the first nozzle portion and forms an air flow path for circulating combustion air between itself and the first nozzle portion;
a swirler arranged in the air flow path and imparting a swirling force to swirl the combustion air flowing through the air flow path around the axis;
a guide section that guides the combustion air that has passed through the swirler to an opening that surrounds an injection region in which the first nozzle section injects the first liquid fuel;
It is formed in a cylindrical shape along the axis and is arranged on the outer peripheral side of the cylindrical portion, and circulates a mixture of atomized second liquid fuel and combustion air between the cylindrical portion and the cylindrical portion. a second nozzle part;
The guide part guides part of the combustion air guided to the opening by the guide part directly to the outer peripheral surface of the guide part on the side of the combustion chamber without passing through the opening. A fuel nozzle with a mechanism. 2. The fuel nozzle according to claim 1, wherein the guide portion has a convex outer peripheral surface whose outer diameter gradually decreases toward the opening along the axis. a pressure-injection type first nozzle portion that is arranged along the axis and injects the first liquid fuel from the injection hole toward the combustion chamber to atomize it;
a cylindrical portion that is formed in a cylindrical shape along the axis and is disposed on the outer peripheral side of the first nozzle portion and forms an air flow path for circulating combustion air between itself and the first nozzle portion;
a swirler arranged in the air flow path and imparting a swirling force to swirl the combustion air flowing through the air flow path about the axis;
a guide section that guides the combustion air that has passed through the swirler to an opening that surrounds an injection region in which the first nozzle section injects the first liquid fuel;
It is formed in a cylindrical shape along the axis and is arranged on the outer peripheral side of the cylindrical portion, and circulates a mixture of atomized second liquid fuel and combustion air between the cylindrical portion and the cylindrical portion. a second nozzle part;
the guide portion has an air circulation mechanism that guides part of the combustion air guided to the injection region by the guide portion directly to the combustion chamber without passing through the opening;
The air flow mechanism is a fuel nozzle that imparts a swirling force to the combustion air led to the combustion chamber to swirl around the axis. a pressure-injection type first nozzle portion that is arranged along the axis and injects the first liquid fuel from the injection hole toward the combustion chamber to atomize it;
a cylindrical portion that is formed in a cylindrical shape along the axis and is disposed on the outer peripheral side of the first nozzle portion and forms an air flow path for circulating combustion air between itself and the first nozzle portion;
a swirler arranged in the air flow path and imparting a swirling force to swirl the combustion air flowing through the air flow path about the axis;
a guide section that guides the combustion air that has passed through the swirler to an opening that surrounds an injection region in which the first nozzle section injects the first liquid fuel;
It is formed in a cylindrical shape along the axis and is arranged on the outer peripheral side of the cylindrical portion, and circulates a mixture of atomized second liquid fuel and combustion air between the cylindrical portion and the cylindrical portion. a second nozzle portion;
A direction that connects an end portion of the cylinder portion on the combustion chamber side and an end portion of the guide portion on the cylinder portion side and directs the air-fuel mixture guided from the second nozzle portion to the combustion chamber away from the axis. and an enlarged diameter portion whose outer diameter gradually expands toward the combustion chamber so as to lead to the combustion chamber ,
The guide portion has an air circulation mechanism that directly guides part of the combustion air guided to the injection region by the guide portion to the combustion chamber without passing through the opening. 5. The fuel nozzle according to any one of claims 1 to 4, wherein the air circulation mechanism is a through-hole formed at a plurality of locations of a structure that does not pass combustion air . a pressure-injection type first nozzle portion that is arranged along the axis and injects the first liquid fuel from the injection hole toward the combustion chamber to atomize it;
a cylindrical portion that is formed in a cylindrical shape along the axis and is disposed on the outer peripheral side of the first nozzle portion and forms an air flow path for circulating combustion air between itself and the first nozzle portion;
a swirler arranged in the air flow path and imparting a swirling force to swirl the combustion air flowing through the air flow path about the axis;
a guide section that guides the combustion air that has passed through the swirler to an opening that surrounds an injection region in which the first nozzle section injects the first liquid fuel;
It is formed in a cylindrical shape along the axis and is arranged on the outer peripheral side of the cylindrical portion, and circulates a mixture of atomized second liquid fuel and combustion air between the cylindrical portion and the cylindrical portion. a second nozzle part;
the guide portion has an air circulation mechanism that guides part of the combustion air guided to the injection region by the guide portion directly to the combustion chamber without passing through the opening;
The air circulation mechanism is a fuel nozzle, which is a porous structure in which air circulation holes are uniformly formed to guide part of the combustion air guided to the injection region directly to the combustion chamber. a pressure-injection type first nozzle portion that is arranged along the axis and injects the first liquid fuel from the injection hole toward the combustion chamber to atomize it;
a cylindrical portion that is formed in a cylindrical shape along the axis and is disposed on the outer peripheral side of the first nozzle portion and forms an air flow path for circulating combustion air between itself and the first nozzle portion;
a swirler arranged in the air flow path and imparting a swirling force to swirl the combustion air flowing through the air flow path about the axis;
a guide section that guides the combustion air that has passed through the swirler to an opening that surrounds an injection region in which the first nozzle section injects the first liquid fuel;
It is formed in a cylindrical shape along the axis and is arranged on the outer peripheral side of the cylindrical portion, and circulates a mixture of atomized second liquid fuel and combustion air between the cylindrical portion and the cylindrical portion. a second nozzle part;
the guide portion has an air circulation mechanism that guides part of the combustion air guided to the injection region by the guide portion directly to the combustion chamber without passing through the opening;
The swirler includes a plurality of swirl vanes circumferentially spaced about the axis. a pressure-injection type first nozzle portion that is arranged along the axis and injects the first liquid fuel from the injection hole toward the combustion chamber to atomize it;
a cylindrical portion that is formed in a cylindrical shape along the axis and is disposed on the outer peripheral side of the first nozzle portion and forms an air flow path for circulating combustion air between itself and the first nozzle portion;
a swirler arranged in the air flow path and imparting a swirling force to swirl the combustion air flowing through the air flow path about the axis;
a guide section that guides the combustion air that has passed through the swirler to an opening that surrounds an injection region in which the first nozzle section injects the first liquid fuel;
It is formed in a cylindrical shape along the axis and is arranged on the outer peripheral side of the cylindrical portion, and circulates a mixture of atomized second liquid fuel and combustion air between the cylindrical portion and the cylindrical portion. a second nozzle part;
the guide portion has an air circulation mechanism that guides part of the combustion air guided to the injection region by the guide portion directly to the combustion chamber without passing through the opening;
The swirler is an annular member arranged between the outer peripheral surface of the first nozzle portion and the inner peripheral surface of the tubular portion,
A fuel nozzle, wherein the annular member is formed with a plurality of orbital holes spaced apart in a circumferential direction about the axis. a combustor comprising the fuel nozzle according to any one of claims 1 to 8, which atomizes and burns the first liquid fuel and the second liquid fuel;
a turbine in which the combustor is driven by combustion gases produced by combusting the first liquid fuel and the second liquid fuel.

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