JP2006336997A - Combustion burner for gas turbine - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To secure good combustion by effectively atomizing and evaporating liquid fuel. <P>SOLUTION: This combustion burner for the gas turbine is provided with a fuel nozzle 110 comprising a plurality of swirlers 130 on its outer peripheral face, in a burner cylinder 120 with a clearance 121. Each swirler 130 is gradually curved from an upstream side toward a downstream side (inclined along circumferential direction) to swirl compressed air A circulated in an air passage 111 to make swirled airflow a. The fuel nozzle 110 is provided with an injection hole 133 for injecting liquid fuel toward blade belly faces of the swirlers 130. The liquid fuel injected from the injection hole 133 is expanded and thinned on a blade face, and sheared by the airflow to be atomized and evaporated. Thus good combustion can be performed by the atomized and evaporated liquid fuel. <P>COPYRIGHT: (C)2007,JPO&INPIT

Description

  The present invention relates to a combustion burner for a gas turbine. In the present invention, even when liquid fuel is used as the fuel for the gas turbine, the liquid fuel is effectively evaporated and atomized (gasified) so as to achieve good combustion. The present invention can be applied not only to oil tank gas turbines that use only liquid fuel as fuel, but also to dual tank gas turbines that use both liquid fuel and gas fuel as fuel.

  A gas turbine used for power generation or the like includes a compressor, a combustor, and a turbine as main members. Many gas turbines have a plurality of combustors, and the air compressed by the compressor and the fuel supplied to the combustors are mixed and burned in each combustor to produce high-temperature combustion gas. generate. The high-temperature combustion gas is supplied to the turbine to drive the turbine.

Here, an example of a conventional combustor of a gas turbine will be described with reference to FIG.
As shown in FIG. 19, a plurality of combustors 10 of a gas turbine are arranged in a ring shape in a combustor casing 11 (only one is shown in FIG. 19). The combustor casing 11 and the gas turbine casing 12 are filled with compressed air to form a passenger compartment 13. Air that has been compressed by a compressor is introduced into the passenger compartment 13. The introduced compressed air enters the inside of the combustor 10 from an air inlet 14 provided in the upstream portion of the combustor 10. Inside the inner cylinder 15 of the combustor 10, the fuel supplied from the fuel nozzle 16 and the compressed air are mixed and burned. The combustion gas generated by the combustion is supplied to the turbine chamber side through the tail cylinder 17 and rotates the turbine rotor.

JP-A-11-14055 JP200412039

As fuel for the gas turbine, not only gas fuel but also liquid fuel is used. In the case of using liquid fuel, conventionally, liquid fuel is injected from the injection hole toward the compressed air flow. In this way, the injected liquid fuel is sheared by the compressed air flow, atomized and mixed with the air. And the atomized liquid fuel mixed with air burns.
As the liquid fuel, there are so-called oil fuels such as A heavy oil, light oil, and dimethyl ether.

  However, in the above-described prior art, the particle size of the granulated liquid fuel is large and the atomization of the liquid fuel is insufficient. For this reason, it has been an impediment to forming a stable flame.

  An object of the present invention is to provide a combustion burner for a gas turbine, which can effectively vaporize and vaporize the liquid fuel when the liquid fuel is used.

The configuration of the present invention for solving the above problems is as follows.
A fuel nozzle;
A burner cylinder which is disposed in a state surrounding the fuel nozzle and forms an air passage with the fuel nozzle;
An upstream side is disposed at a plurality of locations along the circumferential direction of the outer peripheral surface of the fuel nozzle in a state along the axial direction of the fuel nozzle, and swirls the air flowing through the air passage from the upstream side to the downstream side. A swirling blade that is gradually curved toward the downstream side from
A combustion burner for a gas turbine having
The fuel nozzle is formed with an injection hole for injecting liquid fuel toward the blade surface of the swirl blade.

in this case,
The injection hole injects liquid fuel toward the blade belly surface of the swirl wing,
The injection hole injects liquid fuel toward the back surface of the swirl wing,
The circumferential distance between the line where the inner peripheral side of the swirl blade and the fuel nozzle are in contact with the injection hole is within 10 mm,
The injection hole injects liquid fuel toward the leading edge of the swirl blade,
The injection hole injects liquid fuel toward the trailing edge of the swirl wing,
The trailing edge of the swirl wing is formed in a zigzag shape.

The configuration of the present invention is as follows.
A fuel nozzle;
A burner cylinder which is disposed in a state surrounding the fuel nozzle and forms an air passage with the fuel nozzle;
An upstream side is disposed at a plurality of locations along the circumferential direction of the outer peripheral surface of the fuel nozzle in a state along the axial direction of the fuel nozzle, and swirls the air flowing through the air passage from the upstream side to the downstream side. A swirling blade that is gradually curved toward the downstream side from
A combustion burner for a gas turbine having
On the blade abdominal surface of the swirl wing, a stepped portion that is gradually curved from the front edge side toward the rear edge side as it goes from the inner periphery side to the outer periphery side while being recessed on the blade back side is formed,
The fuel nozzle is formed with an injection hole for injecting liquid fuel toward the stepped portion of the blade surface of the swirl blade.

The configuration of the present invention is as follows.
A fuel nozzle;
A burner cylinder which is disposed in a state surrounding the fuel nozzle and forms an air passage with the fuel nozzle;
An upstream side is disposed at a plurality of locations along the circumferential direction of the outer peripheral surface of the fuel nozzle in a state along the axial direction of the fuel nozzle, and swirls the air flowing through the air passage from the upstream side to the downstream side. A swirling blade that is gradually curved toward the downstream side from
A combustion burner for a gas turbine having
The outer peripheral surface of the fuel nozzle includes a splitter blade that is positioned between adjacent swirling blades in the circumferential direction of the fuel nozzle and extends in the axial direction of the fuel nozzle,
The fuel nozzle is formed with an injection hole for injecting liquid fuel toward the blade surface of the splitter blade.

The configuration of the present invention is as follows.
A fuel nozzle;
A burner cylinder which is disposed in a state surrounding the fuel nozzle and forms an air passage with the fuel nozzle;
An upstream side is disposed at a plurality of locations along the circumferential direction of the outer peripheral surface of the fuel nozzle in a state along the axial direction of the fuel nozzle, and swirls the air flowing through the air passage from the upstream side to the downstream side. A swirling blade that is gradually curved toward the downstream side from
A combustion burner for a gas turbine having
Each swirl is divided into a front side and a rear side with respect to the axial direction of the fuel nozzle,
In the outer peripheral surface of the fuel nozzle, an injection hole for injecting liquid fuel toward the front edge of the rear swirl blade is formed at a position between the divided front swirl blade and the rear swirl blade. It is characterized by being.

The configuration of the present invention is as follows.
A fuel nozzle;
A burner cylinder which is disposed in a state surrounding the fuel nozzle and forms an air passage with the fuel nozzle;
An upstream side is disposed at a plurality of locations along the circumferential direction of the outer peripheral surface of the fuel nozzle in a state along the axial direction of the fuel nozzle, and swirls the air flowing through the air passage from the upstream side to the downstream side. A swirling blade that is gradually curved toward the downstream side from
A combustion burner for a gas turbine having
A spraying member that is in a state of surrounding the outer peripheral surface of the fuel nozzle by taking a space between the outer peripheral surface of the fuel nozzle,
The fuel nozzle is formed with an injection hole for injecting liquid fuel toward the inner peripheral surface of the spray member.

The configuration of the present invention is as follows.
In the combustion burner of the gas turbine configured as described above,
The angle formed between the tangent line that contacts the average warp line of the swirl blade at the trailing edge of the swirl blade and the axis along the axial direction of the fuel nozzle is 0 to 10 on the inner peripheral side of the trailing edge of the swirl blade. It is 25 degree | times on the outer peripheral side of the trailing edge of the said swirl | wing blade, It is characterized by the above-mentioned.

The configuration of the present invention is as follows.
In the combustion burner of the gas turbine configured as described above,
The swirl vane or the fuel nozzle is provided with a gas fuel injection hole for injecting gas fuel.

According to the present invention, since the liquid fuel injected from the injection hole is injected to the blade surface such as the swirling blade, the liquid fuel spreads on the blade surface and is thinned, and the thinned liquid fuel is sheared by the high-speed air flow. It is atomized and evaporated.
As described above, the novel configuration in which the liquid fuel is sprayed onto the blade surface can promote effective evaporation of the liquid fuel and ensure good combustion.

Hereinafter, embodiments of the present invention will be described in detail based on examples.
The inventor of the present application has developed a premixed combustion burner for a gas turbine having a novel configuration in which swirler vanes are provided on the outer peripheral surface of the fuel nozzle. The newly developed premixed combustion burner can sufficiently mix the fuel to obtain a uniform concentration of the fuel gas, and can uniformly prevent the backfire by making the flow rate of the fuel gas uniform.
In the following embodiment, an embodiment in which the present invention is applied to the novel premixed combustion burner will be described.

<Overall Configuration of Example 1>
As shown in FIG. 1, a plurality of premixed combustion burners 100 for a gas turbine according to the first embodiment of the present invention are arranged so as to surround the pilot combustion burner 200. Although not shown, the pilot combustion burner 200 incorporates a pilot combustion nozzle.
The premixed combustion burner 100 and the pilot combustion burner 200 are disposed inside the inner cylinder of the gas turbine.

  The premix combustion burner 100 includes a fuel nozzle 110, a burner cylinder 120, and swirl vanes (swirler vanes) 130 as main members.

The burner cylinder 120 is disposed concentrically with the fuel nozzle 110 and surrounds the fuel nozzle 110. Therefore, a ring-shaped air passage 111 is formed between the outer peripheral surface of the fuel nozzle 110 and the inner peripheral surface of the burner cylinder 120.
The compressed air A flows through the air passage 111 from the upstream side (left side in FIG. 1) to the downstream side (right side in FIG. 1).

As shown in FIG. 1, FIG. 2, which is a perspective view, FIG. 3, viewed from the upstream side, and FIG. 4, viewed from the downstream side, the swirl vane 130 has a plurality of locations (6 in this example) along the circumferential direction of the fuel nozzle 110. Are arranged along the axial direction of the fuel nozzle 110.
In FIG. 1, only two swirl vanes 130 arranged at positions of an angle of 0 degrees and an angle of 180 degrees along the circumferential direction are shown for easy understanding (in the state of FIG. You can see four swirl wings).

  Each swirl vane 130 imparts a swirl force to the compressed air A that flows through the air passage 111 to turn the compressed air A into a swirl air flow a. Therefore, each swirl vane 130 is gradually curved (inclined along the circumferential direction) from the upstream side to the downstream side so that the compressed air A can be swirled. Details of the curved state of the swirl vane 130 will be described later.

  A clearance (gap) 121 is provided between the outer peripheral side end face (tip) of each swirl vane 130 and the inner peripheral face of the burner cylinder 120.

  Further, a clearance setting rib 131 is fixed to the front edge side of the outer peripheral side end face (tip) of each swirl vane 130. Each clearance setting rib 131 has a height (radial length) in close contact with the inner peripheral surface of the burner cylinder 120 when the fuel nozzle 110 provided with the swirl vanes 130 is assembled inside the burner cylinder 120. ).

  For this reason, the lengths (radial lengths) of the clearances 121 formed between the swirlers 130 and the burner cylinder 120 are equal. Further, the assembly work when the fuel nozzle 110 provided with the swirl vanes 130 is assembled inside the burner cylinder 120 is facilitated.

  The fuel nozzle 110 is formed with a plurality of injection holes 133 for injecting and spraying fuel toward the blade abdominal surface 132a. Details of the fuel injection hole 133 will be described later.

Here, the curved state of the swirl vane 130 will be described with reference to FIGS.
(1) Generally speaking, each swirl vane 130 is gradually curved from the upstream side toward the downstream side so that the compressed air A can be swirled.
(2) With respect to the axial direction (longitudinal direction of the fuel nozzle 110), the curve becomes larger from the upstream side toward the downstream side.
(3) At the trailing edge of the swirl vane 130, the curvature increases in the radial direction (radial direction (radial direction) of the fuel nozzle 110) toward the outer peripheral side rather than the inner peripheral side.

The above-described curvature at the trailing edge of the swirl vane (3) will be further described with reference to FIG.
In FIG. 5, the dotted line indicates the blade shape (blade cross-sectional shape) on the inner peripheral side (innermost peripheral surface) of the swirl vane 130, and the solid line indicates the blade shape on the outer peripheral side (outermost outer peripheral surface) of the swirl vane 130. (Wing cross-sectional shape) is shown.
In the blade shape on the inner peripheral side indicated by the dotted line, the average warp line (skeleton line) is L11, and the tangent line that contacts the average warp line L11 at the trailing edge of the swirl blade is L12.
In the blade shape on the outer peripheral side indicated by the solid line, the average warp line (skeleton line) is L21, and the tangent line that contacts the average warp line L21 at the trailing edge of the swirl blade is L22.
The axis along the axial direction of the fuel nozzle 110 is L0.

  As shown in FIG. 5, in the present embodiment, at the trailing edge of the swirl vane 130, the angle formed between the tangent line L12 on the inner peripheral side and the axis line L0 is 0 degree, and the tangent line L22 and the axial line L0 on the outer peripheral side are Is made larger than the angle on the inner circumference side.

According to the study of the present inventor, when going from the inner circumference side toward the outer circumference side, when increasing the angle formed between the tangent line and the axis line that contacts the average warp line at the trailing edge of the swirl blade,
(A) The angle on the inner peripheral side is 0 to 10 degrees,
(B) The angle on the outer peripheral side is set to 25 to 35 degrees.
Was determined to be “optimal”.
The term “optimal” here means
(I) Whether the air passage 111 is on the inner peripheral side or the outer peripheral side, the flow rate of the air A (a) is uniform and the occurrence of flashback (backfire) can be prevented.
(Ii) This means that the fuel concentration is uniform regardless of whether it is on the inner peripheral side or the outer peripheral side of the air passage 111.

The reason for the above (i) will be described.
If the angle formed between the tangent line in contact with the average warp line and the axis is the same on the inner peripheral side and the outer peripheral side, streamlines (air flow) from the inner peripheral side to the outer peripheral side are generated. As a result, the flow rate of the air A (a) flowing (circulating along the axial direction) on the inner peripheral side of the air passage 111 becomes slow, and the air A (circulating along the axial direction) flowing on the outer peripheral side of the air passage 111 ( The flow rate of a) becomes faster. In this way, when the air flow rate on the inner peripheral side becomes slow, flashback may occur on the inner peripheral side.

  However, in the present invention, the angle formed between the tangent line that touches the average warp line and the axis line increases as it goes from the inner peripheral side to the outer peripheral side, so that the generation of streamlines from the inner peripheral side to the outer peripheral side is suppressed. Therefore, the flow rate of the air A (a) is uniform and the occurrence of flashback (backfire) can be prevented regardless of whether the air passage 111 is on the inner peripheral side or the outer peripheral side.

The reason for the above (ii) will be described.
The circumferential length of the air passage 111 is short on the inner peripheral side and long on the outer peripheral side. In the present invention, the angle formed between the tangent line that touches the average warp line and the axis line increases as it goes from the inner circumference side toward the outer circumference side, so the force (effect) that imparts swirl to the compressed air A is the circumference length. The outer peripheral side having a longer peripheral length is stronger than the shorter inner peripheral side. As a result, per unit length, the swirl imparting force to the compressed air A is uniform on the inner peripheral side and the outer peripheral side, and the fuel concentration is uniform on the inner peripheral side and the outer peripheral side.

Furthermore, the angle formed by the axis and the tangent line that contacts the average warp line at the trailing edge of the swirl blade,
(A) The angle on the inner peripheral side is specified as 0 to 10 degrees,
(B) The reason for specifying the angle on the outer peripheral side to 25 to 35 degrees,
This will be described with reference to FIGS. 6 and 7 which are characteristic diagrams showing experimental results. The “angle” shown in FIGS. 6 and 7 is an angle formed by a tangent line and an axis line that are in contact with the average warp line at the trailing edge of the swirl blade.

  FIG. 6 is a characteristic diagram in which the vertical axis represents the height (%) of the swirl vane 130 and the horizontal axis represents the flow velocity of the air A (a). The height of the swirl vane of 100% means the outermost peripheral position of the swirl vane, and the swirl vane height of 0% means the innermost peripheral position of the swirl vane.

  FIG. 6 shows the characteristic that the inner peripheral side angle is 0 degree, the outer peripheral side angle is 5 degrees, the inner peripheral side angle is 0 degree, the outer peripheral side angle is 30 degrees, and the inner peripheral side angle. Is 0 degree, the angle on the outer peripheral side is 35 degrees, and the angle on the inner peripheral side and the angle on the outer peripheral side are 20 degrees.

  FIG. 7 is a characteristic diagram in which the vertical axis represents the fuel concentration distribution and the horizontal axis represents the angle on the outer peripheral side. The fuel concentration distribution is the difference between the maximum fuel concentration and the minimum fuel concentration, and means that the concentration is constant as the value of the fuel concentration distribution is smaller.

  FIG. 7 shows a characteristic in which the angle on the inner peripheral side and the angle on the outer peripheral side are 20 degrees, and the characteristic in which the angle on the outer peripheral side is changed by setting the angle on the inner peripheral side to 0 degrees.

As can be seen from FIG. 7 showing the fuel concentration distribution, the fuel concentration becomes uniform when the angle on the outer peripheral side becomes 25 degrees or more.
Further, as can be seen from FIG. 6, when the angle on the outer peripheral side is 25 degrees or more, the distribution of the flow velocity in the blade height direction is uniform because the angle on the inner peripheral side is 0 to 10 degrees and the angle on the outer peripheral side. Is 25 to 35 degrees.

Thus, from the characteristics of FIG. 6 and FIG.
(A) The angle on the inner peripheral side is 0 to 10 degrees,
(B) By setting the angle on the outer peripheral side to 25 to 35 degrees,
(I) Whether the air passage 111 is on the inner peripheral side or the outer peripheral side, the flow rate of the air A (a) is uniform and the occurrence of flashback (backfire) can be prevented.
(Ii) It is understood that the fuel concentration can be made uniform regardless of whether the air passage 111 is on the inner peripheral side or the outer peripheral side.

As described above, in this embodiment, a clearance (gap) 121 is intentionally provided between the outer peripheral side end face (tip) of each swirl vane 130 and the inner peripheral face of the burner cylinder 120.
The blade back surface 132b of the swirl blade 130 has a negative pressure, the blade belly surface 132a has a positive pressure, and there is a pressure difference between the blade back surface 132b and the blade belly surface 132a. For this reason, an air leakage flow is generated through the clearance 121 and from the blade back surface 132a to the blade back surface 132b. This leakage flow and the compressed air A flowing in the axial direction in the air passage 111 act to generate a vortex air flow. By this vortex air flow, the atomized fuel injected from the injection hole 133 toward the blade abdominal surface 133a and evaporated and the air are more effectively mixed, and the homogenization of the fuel gas is promoted.

<Detailed Description of Injection Hole in Example 1>
In the present embodiment, as described above, the fuel nozzle 110 is formed with a plurality of injection holes 133 for injecting fuel. The arrangement position of the injection hole 133 is a position close to each blade abdominal surface 132 a of each swirl blade 130 on the outer periphery of the fuel nozzle 110. Regarding the circumferential direction, the distance between the line where the inner peripheral side of each swirl 130 and the fuel nozzle 110 are in contact with the injection hole 133 is set to be within 10 mm.

  Although not shown, a fuel passage is formed inside the fuel nozzle 110, and liquid fuel is supplied to each injection hole 133 through the fuel passage.

  In this embodiment, the position and orientation of the injection hole 133 are set so that the liquid fuel injected from each injection hole 133 is sprayed to the blade abdominal surface 132a of each swirl vane 130. In the present embodiment, the blade abdominal surface 132a is curved more gradually from the inner peripheral side to the outer peripheral side (toward the radial direction), so liquid fuel is supplied from each injection hole 133 in the radial direction (radial direction). By simply injecting, fuel is sprayed onto the blade surface 132a, and the liquid fuel spreads in a thin film on the blade surface.

  The liquid fuel sprayed on the blade surface 132a spreads on the blade surface and becomes a thin film. The liquid fuel that has spread out on the blade surface and made into a thin film evaporates when it touches the air A (or air a) that is at a high temperature and a high-speed flow. That is, the liquid fuel spread and thinned on the blade belly surface 132a is peeled off and evaporated by the shearing force due to the steep velocity gradient of the airflow boundary layer on the blade belly surface 132a side.

  The thinned liquid fuel evaporates as described above, but the liquid fuel that does not evaporate moves from the blade leading edge toward the blade trailing edge while spreading on the blade surface. The thinned liquid fuel that has reached the blade trailing edge is peeled off from the blade trailing edge by the high-speed air A (a) and atomized. At this time, since the oil film thickness of the thinned liquid fuel is extremely thin, the particle size of the atomized liquid fuel becomes extremely small, and the liquid fuel having the fine particle size is swirling air flow a (including vortex air flow). Evaporation is promoted by mixing with.

  Thus, by injecting the liquid fuel onto the blade abdominal surface 132a, atomization and evaporation of the liquid fuel can be promoted, and the evaporated liquid fuel becomes a fine particle size and is mixed with air and burned. For this reason, favorable combustion can be performed.

  Each swirl vane 130 or fuel nozzle 110 is provided with a gas fuel injection hole for injecting gas fuel. The gas fuel is injected from the gas fuel injection hole and from the injection hole 133 toward the blade belly surface 132a. A dual soot gas turbine in which liquid fuel is injected and gas fuel and liquid fuel are burned simultaneously may be used.

In a normal (conventional) dual soot gas turbine, a gas fuel nozzle and a liquid fuel nozzle are provided separately, but in this embodiment, the dual soot gas turbine is provided with an injection hole 133 for liquid fuel. Therefore, the nozzle structure can be simplified.
That is, as the configuration for liquid fuel, it is only necessary to provide the injection hole 133, and the liquid fuel injected from the injection hole 133 is sprayed on the blade surface, and the liquid fuel can be obtained without a special liquid fuel nozzle structure. Can be atomized and evaporated.

  In the present embodiment, with respect to the circumferential direction, the distance between the line where the inner peripheral side of each swirl 130 is in contact with the fuel nozzle 110 and the injection hole 133 is within 10 mm. For this reason, the liquid fuel injected from the injection hole 133 is sprayed to the blade belly surface 132a as soon as possible after the discharge. That is, the distance over which the liquid fuel in the liquid column state is injected is minimized. For this reason, even if the liquid fuel in the liquid column state is injected into the space of the air passage 110, the influence on the air flow of the air A (a) flowing through the air passage 110 can be minimized.

<Modification of injection hole>
In the example described above, the fuel nozzle 110 is provided with the injection hole 133 for injecting the liquid fuel to the blade abdominal surface 132a, but the fuel nozzle 110 is provided with the injection hole for injecting the liquid fuel to each blade back surface 132b of each swirl blade 130. It may be.
As described above, when the liquid fuel is injected onto the blade back surface 132b, the fine particles of the liquid fuel spread in a thin film form on the blade surface due to the secondary flow vortex of the air from the inner peripheral side that rolls up along the blade back surface 132b. And evaporation can be promoted.

  Of course, both the injection hole 133 for injecting liquid fuel to the blade abdominal surface 132a of the swirl blade 130 and the injection hole for injecting liquid fuel to the blade back surface 132b may be provided.

Furthermore, while providing the injection hole 133 which injects liquid fuel to a blade surface, as shown in FIG.8 and FIG.9, you may make it form the trailing edge of the swirl | wing blade 130 in zigzag.
When the trailing edge of the swirl vane 130 is formed in a zigzag in this way, turbulent flow (small vortex air flow) is generated at the trailing edge of the blade, and mixing and pre-evaporation of the gasified fuel and air a can be promoted. .

  Next, a second embodiment of the present invention will be described. In addition, description is abbreviate | omitted about the component similar to Example 1, and a part peculiar to Example 2 is demonstrated.

  As shown in FIG. 10, in the second embodiment, the fuel nozzle 110 includes a plurality of injection holes 133 a that inject liquid fuel toward the front edge of each swirl vane 130. In the second embodiment, the liquid fuel injected from the injection hole 133a and sprayed on the leading edge of the swirl vane 130 is finely divided by the shearing force due to the steep velocity gradient of the boundary layer of the airflow (compressed air A) hitting the leading edge of the blade. Pre-evaporation can be promoted.

  Next, a third embodiment of the present invention will be described. In addition, description is abbreviate | omitted about the component similar to Example 1, and a part peculiar to Example 3 is demonstrated.

  As shown in FIG. 11, in Example 3, a spraying surface that is a concave surface is formed at the rear edge of each swirl vane 130. The fuel nozzle 110 is provided with a plurality of injection holes 133b for injecting liquid fuel toward the trailing edge of each swirl vane 130. In the third embodiment, since the liquid fuel is atomized and evaporated by the high-speed air flow near the trailing edge of the swirl vane 130, the pre-evaporation can be promoted.

  Next, a fourth embodiment of the present invention will be described. In addition, description is abbreviate | omitted about the component similar to Example 1, and a part peculiar to Example 4 is demonstrated.

  As shown in FIG.12 and FIG.13, in Example 4, the level | step difference 134 is formed in the blade | wing belly surface 132a side. The step 134 is recessed toward the blade back surface 132b side with respect to the surface of the blade abdominal surface 132a. The depth of the step (depression) is 0.3 to 1.0 mm, that is, the thickness of the boundary layer. The depth. Moreover, the step 134 is gradually curved from the front edge side to the rear edge side as it goes from the inner circumference side to the outer circumference side.

In the fourth embodiment, the injection hole 133 c formed in the fuel nozzle 110 injects liquid fuel toward the step 134. The injected liquid fuel blows up along the step 134, spreads on the blade surface, evaporates into a thin film.
Since the liquid fuel blows up along the step 134 in this way, even when the liquid fuel blowing speed is high, the liquid fuel can be prevented from jumping out of the swirl blade 130 to the outside of the blade. Can do. Further, since the range in which the liquid fuel spreads can be limited (specified) by the step 134, the pre-evaporation amount and the downstream concentration distribution can be controlled.
Further, since the depth of the step 134 is a depth corresponding to the thickness of the boundary layer, the air A (a) flowing through the air passage 111 is not adversely affected.

  Next, a fifth embodiment of the present invention will be described. In addition, description is abbreviate | omitted about the component similar to Example 1, and a part peculiar to Example 5 is demonstrated.

  As shown in FIGS. 14 and 15, in the fifth embodiment, not only the swirl vanes 130 but also the splitter vanes 140 are provided on the outer peripheral surface of the fuel nozzle 110. The splitter blade 140 is located between the adjacent swirl blades 130 and 130 in the circumferential direction of the fuel nozzle 110 and extends along the axial direction of the fuel nozzle 110. In other words, the swirl vanes 130 and the splitter vanes 140 are alternately arranged in the circumferential direction of the fuel nozzle 110. The splitter blade 140 rectifies the flow of the compressed air A.

  In the fifth embodiment, the fuel nozzle 110 is provided with an injection hole 133 d for injecting liquid fuel toward the blade surface of the splitter blade 140. For this reason, the liquid fuel injected from the injection hole 133d spreads on the blade surface of the splitter blade 140, evaporates into a thin film.

  Each swirl vane 130 is formed with an injection hole 150 for gas fuel for injecting gas fuel. Gas fuel is supplied to the injection hole 150 for gas fuel via a gas fuel passage (not shown) formed in the fuel nozzle 110 and the swirl vane 130, and the supplied gas fuel is injected from the injection hole 150. .

  In the fifth embodiment, the gas fuel is ejected from the injection hole 150 provided in the swirl vane 130, the liquid fuel is injected from the injection hole 133d, the film is thinned on the blade surface of the splitter blade 140, and evaporated. However, the interference between the gas fuel and the liquid fuel can be minimized and good combustion can be achieved. Further, since there are the splitter blades 140, the airflow of the compressed air A can be adjusted.

  Next, a sixth embodiment of the present invention will be described. In addition, description is abbreviate | omitted about the component similar to Example 1, and a part peculiar to Example 6 is demonstrated.

  As shown in FIG. 16A, in the sixth embodiment, with respect to the axial direction of the fuel nozzle 110, the divided front swirler 130a and rear swirler 130b serve as one swirler. . In the fuel nozzle 110, a liquid fuel injection hole 133e is provided at a position between the two divided blades 130a and 130b. This injection hole 133e blows liquid fuel to the front edge of the rear swirl vane 130b. Thus, since the liquid fuel is injected from the position between the two blades 130a and 130b, the liquid fuel is sprayed to the leading edge of the swirl blade 130b without hitting the air at high speed. The sprayed liquid fuel spreads from the leading edge of the swirl vane 130b to the blade front and back surfaces, promotes pre-evaporation by the shearing effect of the high-speed compressed air A, and atomizes and gasifies.

  Further, the front swirl vane 130a is provided with an injection hole 150a for blowing out gas fuel so that dual soot can be formed.

  In addition, as shown in FIG.16 (b), you may make it make the rear edge of the front turning blade 130a thin.

  Next, a seventh embodiment of the present invention will be described. In addition, description is abbreviate | omitted about the component similar to Example 1, and a part peculiar to Example 7 is demonstrated.

  In the seventh embodiment, as shown in FIGS. 17 and 18, a space is formed between the outer periphery of the fuel nozzle 110 on the front side of the fuel nozzle 110 to surround the outer periphery of the fuel nozzle 110. The spray member 160 is arranged. The front edge side portion of each swirl vane 130 is in a state of biting into the blowing member 160.

  Further, the fuel nozzle 110 is provided with an injection hole 133f for spraying liquid fuel toward the inner peripheral surface of the spray member 160. Moreover, each swirl | wing blade 130 is provided with the injection hole 150b which injects gaseous fuel.

In the seventh embodiment, the liquid fuel injected from the injection hole 133f is sprayed on the inner peripheral surface of the spray member 160 to be thinned, atomized and evaporated. At this time, by appropriately setting the distance (radial direction distance) between the outer peripheral surface of the fuel nozzle 110 and the inner peripheral surface of the blowing member 160, the distribution of the fuel concentration downstream can be controlled.
Further, since the gas fuel is injected on the outer peripheral side of the spray member 160 and the liquid fuel is atomized and evaporated on the inner peripheral surface of the spray member 160, the gas fuel and the liquid fuel are prevented from interfering with each other and good combustion is achieved. Can do.

  In FIG. 17, the blowing member 160 is arranged at the front edge side portion (upstream side) with respect to the axial direction of the fuel nozzle 110, but is arranged at the center portion or the rear edge side portion (downstream side) of the fuel nozzle 110. May be.

  When the blowing member 160 is disposed at the rear edge side portion (downstream side) with respect to the axial direction of the fuel nozzle 110, the occurrence of the turbulence of the compressed air A acting on the gas fuel injected from the injection hole 150b is reduced. be able to.

<Variation of swirl blade>
In each of the above-described embodiments, the swirl vane 130 extends along the tangent line that contacts the average warp line of the swirl vane 130 at the trailing edge of the swirl vane 130 and the axial direction of the fuel nozzle 110, as shown in FIG. The angle formed with the axis is 0 to 10 degrees on the inner peripheral side of the trailing edge of the swirl vane 130, and 25 to 35 degrees on the outer peripheral side of the trailing edge of the swirl vane 130.
The present invention is not limited to the above-described state, and an angle formed by a tangent line that is in contact with the average warp line of the swirl vane 130 at the rear edge of the swirl vane 130 and an axis along the axial direction of the fuel nozzle 110. Needless to say, the present invention can also be applied to the same swirl vane on the inner peripheral side and the outer peripheral side of the rear edge of the swirl vane 130.

The block diagram which shows the combustion burner of the gas turbine based on Example 1 of this invention. 1 is a perspective view showing a fuel nozzle and swirl vanes of a combustion burner according to Embodiment 1. FIG. The block diagram which shows the fuel nozzle and swirl | wing blade of the combustion burner which concerns on Example 1 from an upstream. The block diagram which shows the fuel nozzle and swirl | wing blade of the combustion burner which concerns on Example 1 from the downstream. Explanatory drawing which shows the curved state of a turning blade. The characteristic view which shows the relationship between swirl blade height and air flow velocity. The characteristic view which shows the relationship between fuel concentration distribution and the angle of the outer peripheral side of a turning blade. FIG. 6 is a configuration diagram showing a modification of the first embodiment. FIG. 6 is a perspective view showing a modification of the first embodiment. The perspective view which shows the fuel nozzle and swirl | wing blade of the combustion burner which concerns on Example 2 of this invention. The perspective view which shows the fuel nozzle and swirl | wing blade of the combustion burner which concern on Example 3 of this invention. The perspective view which shows the fuel nozzle and swirl | wing blade of the combustion burner which concerns on Example 4 of this invention. Sectional drawing which shows the swirl | wing blade of the combustion burner which concerns on Example 4 of this invention. The perspective view which shows the fuel nozzle and swirl | wing blade of the combustion burner which concern on Example 5 of this invention. The front view which shows the fuel nozzle and swirl | wing blade of the combustion burner which concern on Example 5 of this invention. The perspective view which shows the fuel nozzle and swirl | wing blade of the combustion burner which concern on Example 6 of this invention. The perspective view which shows the fuel nozzle and swirl | wing blade of the combustion burner which concern on Example 7 of this invention. The front view which shows the fuel nozzle and swirl | wing blade of the combustion burner which concern on Example 7 of this invention. The block diagram which shows the conventional gas turbine.

Explanation of symbols

100 Premixed Combustion Burner 110 Fuel Nozzle 111 Air Passage 120 Burner Tube 121 Clearance 130 Swivel Tube 131 Clearance Setting Rib 132a Blade Abdomen Surface 132b Blade Back Surface 133, 133a to 133f Liquid Fuel Injection Hole 134 Step 140 Splitter Blade 150, 150a, 150b Injection hole for gas fuel 160 Spray member 200 Pilot combustion burner A Compressed air a Swirl air flow

Claims (13)

A fuel nozzle;
A burner cylinder which is disposed in a state surrounding the fuel nozzle and forms an air passage with the fuel nozzle;
An upstream side is disposed at a plurality of locations along the circumferential direction of the outer peripheral surface of the fuel nozzle in a state along the axial direction of the fuel nozzle, and swirls the air flowing through the air passage from the upstream side to the downstream side. A swirling blade that is gradually curved toward the downstream side from
A combustion burner for a gas turbine having
A combustion burner for a gas turbine, wherein an injection hole for injecting liquid fuel toward a blade surface of the swirl blade is formed in the fuel nozzle. 2. The combustion burner for a gas turbine according to claim 1, wherein the injection hole injects liquid fuel toward a blade belly surface of the swirl blade. 2. The combustion burner for a gas turbine according to claim 1, wherein the injection hole injects liquid fuel toward a back surface of the swirl blade. In claim 2 or claim 3,
A combustion burner for a gas turbine, wherein a circumferential distance between a line where the inner peripheral side of the swirl blade is in contact with the fuel nozzle and the injection hole is within 10 mm. 2. The combustion burner for a gas turbine according to claim 1, wherein the injection hole injects liquid fuel toward a leading edge of the swirl vane. 2. A combustion burner for a gas turbine according to claim 1, wherein the injection hole injects liquid fuel toward a rear edge of the swirl blade. In any one of Claims 1 thru | or 6,
A combustion burner for a gas turbine, wherein a rear edge of the swirl vane is formed in a zigzag shape. A fuel nozzle;
A burner cylinder which is disposed in a state surrounding the fuel nozzle and forms an air passage with the fuel nozzle;
An upstream side is disposed at a plurality of locations along the circumferential direction of the outer peripheral surface of the fuel nozzle in a state along the axial direction of the fuel nozzle, and swirls the air flowing through the air passage from the upstream side to the downstream side. A swirling blade that is gradually curved toward the downstream side from
A combustion burner for a gas turbine having
On the blade abdominal surface of the swirl wing, a stepped portion that is gradually curved from the front edge side toward the rear edge side as it goes from the inner periphery side to the outer periphery side while being recessed on the blade back side is formed,
A combustion burner for a gas turbine, wherein the fuel nozzle is formed with an injection hole for injecting liquid fuel toward the stepped portion of the swirl blade. A fuel nozzle;
A burner cylinder which is disposed in a state surrounding the fuel nozzle and forms an air passage with the fuel nozzle;
An upstream side is disposed at a plurality of locations along the circumferential direction of the outer peripheral surface of the fuel nozzle in a state along the axial direction of the fuel nozzle, and swirls the air flowing through the air passage from the upstream side to the downstream side. A swirling blade that is gradually curved toward the downstream side from
A combustion burner for a gas turbine having
The outer peripheral surface of the fuel nozzle includes a splitter blade that is positioned between adjacent swirling blades in the circumferential direction of the fuel nozzle and extends in the axial direction of the fuel nozzle,
A combustion burner for a gas turbine, wherein an injection hole for injecting liquid fuel toward the blade surface of the splitter blade is formed in the fuel nozzle. A fuel nozzle;
A burner cylinder which is disposed in a state surrounding the fuel nozzle and forms an air passage with the fuel nozzle;
An upstream side is disposed at a plurality of locations along the circumferential direction of the outer peripheral surface of the fuel nozzle in a state along the axial direction of the fuel nozzle, and swirls the air flowing through the air passage from the upstream side to the downstream side. A swirling blade that is gradually curved toward the downstream side from
A combustion burner for a gas turbine having
Each swirl is divided into a front side and a rear side with respect to the axial direction of the fuel nozzle,
In the outer peripheral surface of the fuel nozzle, an injection hole for injecting liquid fuel toward the front edge of the rear swirl blade is formed at a position between the divided front swirl blade and the rear swirl blade. A combustion burner for a gas turbine, characterized in that A fuel nozzle;
A burner cylinder which is disposed in a state surrounding the fuel nozzle and forms an air passage with the fuel nozzle;
An upstream side is disposed at a plurality of locations along the circumferential direction of the outer peripheral surface of the fuel nozzle in a state along the axial direction of the fuel nozzle, and swirls the air flowing through the air passage from the upstream side to the downstream side. A swirling blade that is gradually curved toward the downstream side from
A combustion burner for a gas turbine having
A spraying member that is in a state of surrounding the outer peripheral surface of the fuel nozzle by taking a space between the outer peripheral surface of the fuel nozzle,
A combustion burner for a gas turbine, wherein an injection hole for injecting liquid fuel toward the inner peripheral surface of the spray member is formed in the fuel nozzle. In claims 1 to 11,
The angle formed between the tangent line that contacts the average warp line of the swirl blade at the trailing edge of the swirl blade and the axis along the axial direction of the fuel nozzle is 0 to 10 on the inner peripheral side of the trailing edge of the swirl blade. A combustion burner for a gas turbine, characterized in that the angle is 25 to 35 degrees on the outer peripheral side of the trailing edge of the swirl blade. In claims 1 to 12,
A combustion burner for a gas turbine, wherein the swirl vane or the fuel nozzle is provided with a gas fuel injection hole for injecting gas fuel.

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