Patent Grant
7878001
This invention relates to a premixed combustion burner of a gas turbine. The present invention is contrived to be capable of effectively premixing a fuel and air to form a fuel gas of a uniform concentration, and uniformizing the flow velocity of the fuel gas, thereby preventing backfire reliably.
A gas turbine used in power generation, etc. is composed of a compressor, a combustor, and a turbine as main members. The gas turbine often has a plurality of combustors, and mixes air, which is compressed by the compressor, with a fuel supplied to the combustors, and burns the mixture in each combustor to generate a high temperature combustion gas. This high temperature combustion gas is supplied to the turbine to drive the turbine rotationally.
An example of the combustor of a conventional gas turbine will be described with reference to
As shown in
Thus, the fuel injected from the premixing fuel nozzles 16a is premixed with air, which has been converted to a swirl flow by the swirlers 18, and is burned within the inner tube 15.
Patent Document 1: Japanese Unexamined Patent Publication No. 1999-14055
Patent Document 2: Japanese Unexamined Patent Publication No. 2004-12039
The conventional technology shown in
The inventor of the present application developed a different type of a combustion burner, which was a premixed combustion burner of a gas turbine, the burner having swirl vanes (swirler vanes) on the outer peripheral surface of a premixing fuel nozzle.
The premixed combustion burner having swirl vanes on the outer peripheral surface of a premixing fuel nozzle has hitherto been present, but there has been no premixed combustion burner with satisfactory performance which can
(1) thoroughly mix a fuel to form a fuel gas of a uniform concentration, and
(2) uniformize the flow velocity of the fuel gas to prevent backfire reliably.
The inventor diligently conducted studies on a premixed combustion burner having swirl vanes provided on the outer peripheral surface of a premixing fuel nozzle, and developed a premixed combustion burner of a gas turbine having unique features and excellent effects which are absent in conventional technologies. The inventor has decided to file an application for a patent on the results gained.
A constitution of the present invention for solving the above problems is a premixed combustion burner of a gas turbine, the premixed combustion burner comprising:
a fuel nozzle;
a burner tube disposed to encircle the fuel nozzle for forming an air passage between the burner tube and the fuel nozzle; and
swirl vanes which are arranged at a plurality of locations along a circumferential direction of an outer peripheral surface of the fuel nozzle in such a state as to extend along an axial direction of the fuel nozzle, and which progressively curve from an upstream side toward a downstream side for swirling air flowing through the air passage from the upstream side toward the downstream side, characterized in that
an angle formed by a tangent to an average camber line of the swirl vane at a rear edge of the swirl vane and an axis line extending along the axial direction of the fuel nozzle is 0 to 10 degrees on an inner peripheral side of the rear edge of the swirl vane, and the angle is larger on an outer peripheral side of the rear edge of the swirl vane than the angle on the inner peripheral side of the rear edge of the swirl vane.
Another constitution of the present invention is a premixed combustion burner of a gas turbine, the premixed combustion burner comprising:
a fuel nozzle;
a burner tube disposed to encircle the fuel nozzle for forming an air passage between the burner tube and the fuel nozzle; and
swirl vanes which are arranged at a plurality of locations along a circumferential direction of an outer peripheral surface of the fuel nozzle in such a state as to extend along an axial direction of the fuel nozzle, and which progressively curve from an upstream side toward a downstream side for swirling air flowing through the air passage from the upstream side toward the downstream side, characterized in that
an angle formed by a tangent to an average camber line of the swirl vane at a rear edge of the swirl vane and an axis line extending along the axial direction of the fuel nozzle is 0 to 10 degrees on an inner peripheral side of the rear edge of the swirl vane, and is 25 to 35 degrees on an outer peripheral side of the rear edge of the swirl vane.
Another constitution of the present invention is a premixed combustion burner of a gas turbine, the premixed combustion burner comprising:
a fuel nozzle;
a burner tube disposed to encircle the fuel nozzle for forming an air passage between the burner tube and the fuel nozzle; and
swirl vanes which are arranged at a plurality of locations along a circumferential direction of an outer peripheral surface of the fuel nozzle in such a state as to extend along an axial direction of the fuel nozzle, and which progressively curve from an upstream side toward a downstream side for swirling air flowing through the air passage from the upstream side toward the downstream side, characterized in that
a clearance is provided between an outer peripheral side end surface of the swirl vane and an inner peripheral surface of the burner tube.
Another constitution of the present invention is the premixed combustion burner of a gas turbine according to any one of the above constitutions, characterized in that
a clearance is provided between an outer peripheral side end surface of the swirl vane and an inner peripheral surface of the burner tube, and
a ratio between a vane height of the swirl vane and a length of the clearance (clearance length/vane height) is set at 1 to 10%.
Another constitution of the present invention is the premixed combustion burner of a gas turbine according to any one of the above constitutions, characterized in that
in order to render a clearance between an outer peripheral side end surface of the swirl vane and an inner peripheral surface of the burner tube constant, a clearance setting rib, which makes intimate contact with the inner peripheral surface of the burner tube, is provided at a portion of the outer peripheral side end surface of the swirl vane.
Another constitution of the present invention is the premixed combustion burner of a gas turbine according to any one of the above constitutions, characterized in that
an aspect ratio between a vane chord length and the vane height of the swirl vane (vane height/vane chord length) is set at 0.2 to 0.75.
Another constitution of the present invention is the premixed combustion burner of a gas turbine according to any one of the above constitutions, characterized in that
a vane thickness of the swirl vane is a length which is 0.1 to 0.3 times a vane chord length of the swirl vane.
Another constitution of the present invention is the premixed combustion burner of a gas turbine according to any one of the above constitutions, characterized in that
a vane thickness at the rear edge of the swirl vane is smaller than 0.2 times a throat length.
Another constitution of the present invention is the premixed combustion burner of a gas turbine according to any one of the above constitutions, characterized in that
fuel injection holes for injecting a fuel supplied from the fuel nozzle through fuel passages are formed in the swirl vane, and
the fuel injection holes formed in opposed vane surfaces of the adjacent swirl vanes are positioned such that positions of the fuel injection holes formed in one of the vane surfaces, and positions of the fuel injection holes formed in the other vane surface are displaced with respect to each other.
According to the present invention, the angle formed by the tangent to the average camber line of the swirl vane at the rear edge of the swirl vane and the axis line extending along the axial direction of the fuel nozzle is 0 to 10 degrees on the inner peripheral side of the rear edge of the swirl vane, and the angle is larger (25 to 35 degrees) on the outer peripheral side of the rear edge of the swirl vane than the angle on the inner peripheral side of the rear edge of the swirl vane. Thus, whether on the inner peripheral side or on the outer peripheral side of the air passage, the flow velocity of air becomes uniform, the occurrence of backfire can be prevented, and the fuel concentration becomes uniform.
According to the present invention, moreover, the clearance is provided between the outer peripheral side end surface of the swirl vane and the inner peripheral surface of the burner tube. Thus, a vortex air flow is produced by the action of a leakage flow, which passes through the clearance and flows from the vane dorsal surface to the vane ventral surface, and a flow in the axial direction, and this vortex air flow can promote the mixing of the fuel and air.
a), 8(b)
a) to 9(d) are explanation drawings showing the relationships between the swirl vanes having different aspect ratios and vortex air flows.
Embodiments of the present invention will now be described in detail based on the Embodiments shown below.
A plurality of premixed combustion burners 100 of a gas turbine according to Embodiment 1 of the present invention are arranged to surround the periphery of a pilot combustion burner 200, as shown in
The premixed combustion burners 100, and the pilot combustion burner 200 are arranged within the inner tube of the gas turbine.
The premixed combustion burner 100 is composed of a fuel nozzle 110, a burner tube 120, and a swirl vane (swirler vane) 130 as main members.
The burner tube 120 is disposed to be concentric with the fuel nozzle 110 and to encircle the fuel nozzle 110. Thus, 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 tube 120.
Compressed air A flows through the air passage 111 from its upstream side (left-hand side in
As shown in
In
Each swirl vane 130 is designed to impart a swirling force to the compressed air A flowing through the air passage 111, thereby converting the compressed air A into a swirl air flow a. For this purpose, each swirl vane 130 gradually curves from its upstream side toward its downstream side (inclines along the circumferential direction) so as to be capable of swirling the compressed air A. 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 surface (tip) of each swirl vane 130 and the inner peripheral surface of the burner tube 120.
Further, a clearance setting rib 131 is fixed to a front edge side of the outer peripheral side end surface (tip) of each swirl vane 130. Each clearance setting rib 131 has such a height (diametrical length) as to make intimate contact with the inner peripheral surface of the burner tube 120 when the fuel nozzle 110 equipped with the swirl vanes 130 is assembled to the interior of the burner tube 120.
Thus, the length (diametrical length) of each clearance 121 formed between each swirl vane 130 and the burner tube 120 is equal. Also, it becomes easy to perform an assembly operation for assembling the fuel nozzle 110 equipped with the swirl vanes 130 to the interior of the burner tube 120.
The relationship between the length of the clearance 121 and the vane height of the swirl vane 130 will be described later.
Injection holes 133b (indicated by dashed-line circles in
Thus, when the adjacent swirl vanes 131 are observed, the position of the injection hole 133a formed in the vane ventral surface 132a of one of the adjacent swirl vanes 131 and the position of the injection hole 133b formed in the vane dorsal surface 132b of the other of the adjacent swirl vanes 131 are displaced with respect to each other.
Fuel passages, although not shown, are formed within the fuel nozzle 110 and each swirl vane 130, and a fuel is supplied to the respective injection holes 133a, 133b via the fuel passages of the fuel nozzle 110 and the fuel passages of each swirl vane 130.
Thus, the fuel is injected through the respective injection holes 133a, 133b toward the air passage 111. At this time, the position of arrangement of the injection hole 133a and the position of arrangement of the injection hole 133b are displaced with respect to each other, so that the fuel injected through the injection hole 133a and the fuel injected through the injection hole 133b do not interfere (collide).
The injected fuel is mixed with the air A (a) to form a fuel gas, which is fed to the internal space of an inner tube for combustion.
Next, the curved state of the swirl vane 130 will be described with reference to
(1) Briefly, each swirl vane 130 progressively curves from its upstream side toward its downstream side so as to be capable of swirling the compressed air A.
(2) As far as the axial direction (longitudinal direction of the fuel nozzle 110) is concerned, the curvature increases farther from the upstream side and nearer to the downstream side.
(3) At the rear edge of the swirl vane 130, the curvature increases toward the outer peripheral side, as compared with the inner peripheral side, with respect to the diametrical direction (radial direction (direction of radiation) of the fuel nozzle 110).
The above-described curvature at the rear edge of the swirl vane 130 in (3) will be further described with reference to
In
In the vane profile on the inner peripheral side indicated by the dashed lines, an average camber line (skeletal line) is designated as L11, and a tangent to the average camber line L11 at the rear edge of the swirl vane is designated as L12.
In the vane profile on the outer peripheral side indicated by the solid lines, an average camber line (skeletal line) is designated as L21, and a tangent to the average camber line L21 at the rear edge of the swirl vane is designated as L22.
An axis line along the axial direction of the fuel nozzle 110 is designated as L0.
According to the present embodiment, as shown in
According to studies by the inventor, when the angle formed by the axis line and the tangent to the average camber line at the rear edge of the swirl vane is increased from the inner peripheral side toward the outer peripheral side, it has been found “optimal”
(a) to set the angle on the inner peripheral side at 0 to 10 degrees, and
(b) to set the angle on the outer peripheral side at 25 to 35 degrees.
Here, the term “optimal” means
(i) that whether on the inner peripheral side or on the outer peripheral side of the air passage 111, the flow velocity of the air A (a) becomes uniform, and the occurrence of flashback (backfire) can be prevented, and
(ii) that whether on the inner peripheral side or on the outer peripheral side of the air passage 111, the fuel concentration becomes uniform.
The reason for (i) will be described.
Assume that the angle formed by the tangent to the average camber line and the axis line on the inner peripheral side is set to be equal to that on the outer peripheral side. In this case, a streamline (air flow) heading from the inner peripheral side toward the outer peripheral side is generated. As a result, the flow velocity of the air A (a) passing on the inner peripheral side of the air passage 111 (passing along the axial direction) becomes low, while the flow velocity of the air A (a) passing on the outer peripheral side of the air passage 111 (passing along the axial direction) becomes high. If the air flow velocity on the inner peripheral side is decreased in this manner, flashback is likely to occur on the inner peripheral side.
In the present invention, however, the angle formed by the tangent to the average camber line and the axis line increases from the inner peripheral side toward the outer peripheral side. Thus, the occurrence of the streamline heading from the inner peripheral side toward the outer peripheral side can be suppressed. Whether on the inner peripheral side or on the outer peripheral side of the air passage 111, therefore, the flow velocity of the air A (a) becomes uniform, and can prevent the occurrence of flashback (backfire).
The reason for (ii) above 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 by the tangent to the average camber line and the axis line increases from the inner peripheral side toward the outer peripheral side. Thus, the force (effect) imparting swirl to the compressed air A is stronger on the outer peripheral side with the larger circumferential length than on the inner peripheral side with the smaller circumferential length. As a result, the force imparting swirl to the compressed air A is uniform, per unit length, not only on the inner peripheral side but also on the outer peripheral side. Thus, the fuel concentration is uniform on the outer peripheral side as well as on the inner peripheral side.
Furthermore, the reason why the angle formed by the axis line and the tangent to the average camber line at the rear edge of the swirl vane is
(a) set at 0 to 10 degrees as the angle on the inner peripheral side, and
(b) set at 25 to 35 degrees as the angle on the outer peripheral side
will be explained with reference to
As seen from
As seen from
As note above, the characteristics in
(a) by setting the angle on the inner peripheral side at 0 to 10 degrees, and
(b) by setting the angle on the outer peripheral side at 25 to 35 degrees,
(i) whether on the inner peripheral side or on the outer peripheral side of the air passage 111, the flow velocity of the air A (a) becomes uniform, and can prevent the occurrence of flashback (backfire), and
(ii) whether on the inner peripheral side or on the outer peripheral side of the air passage 111, the fuel concentration can be uniformized.
In the present embodiment, as stated above, the clearance (gap) 121 is intentionally provided between the outer peripheral side end surface (tip) of each swirl vane 130 and the inner peripheral surface of the burner tube 120.
The vane dorsal surface 132b of the swirl vane 130 is under negative pressure, while the vane ventral surface 132a of the swirl vane 130 is under positive pressure, so that there is a pressure difference between the vane dorsal surface 132b and the vane ventral surface 132a. Thus, a leakage flow of air is produced which passes through the clearance 121 and goes around from the vane ventral surface 132a to the vane dorsal surface 132b. This leakage flow, and the compressed air A flowing through the air passage 111 in the axial direction act to produce a vortex air flow. This vortex air flow mixes the fuel injected through the injection holes 133a, 133b and air more effectively, thereby promoting the uniformization of the fuel gas.
In the present embodiment, the ratio between the vane height of the swirl vane 130 and the length of the clearance 121 (clearance length/vane height) is set at 1 to 10%. By so doing, the uniformization of the concentration distribution of the fuel can be promoted, without an increase in the pressure loss.
The reason why the uniformization of the concentration distribution of the fuel can be promoted, without an increase in the pressure loss, by setting the ratio (clearance length/vane height) at 1 to 10% will be described with reference to
a) is a characteristic view in which the fuel concentration distribution is plotted as the ordinate and the ratio (clearance length/vane height) is plotted as the abscissa. The fuel concentration distribution refers to the difference between the maximum fuel concentration and the minimum fuel concentration, and a smaller value of the fuel concentration distribution means that the concentration is constant.
b) is a characteristic view in which the loss is plotted as the ordinate and the ratio (clearance length/vane height) is plotted as the abscissa.
As seen from
After all, it is recommendable that the ratio (clearance length/vane height) be 1 to 10%, in order to promote mixing by the vortex air flow, while controlling the flow, without increasing the pressure loss, thereby uniformizing the concentration distribution of the fuel.
Ideally, the ratio (clearance length/vane height) should be 7 to 10%.
In the present embodiment, moreover, an aspect ratio between the vane chord length (chord length) c and the vane height h of the swirl vane 130 (vane height h/vane chord length c) is set at 0.2 to 0.75 (see
In the present embodiment, as stated earlier, the leakage flow of air, which passes through the clearance 121 and goes around from the vane dorsal surface 132b to the vane ventral surface 132a, and the compressed air A flowing in the axial direction act to produce the vortex air flow u.
When the aspect ratio h/c is set at 0.2 to 0.75, the region of mixing by the vortex air flow u corresponds to 50% or more of the vane height h, as shown in
An aspect ratio h/c of about 0.5 is optimal.
If the aspect ratio h/c is higher than 0.75, the region of mixing by the vortex air flow u corresponds to less than 50% of the vane height h, as shown in
If the aspect ratio h/c is lower than 0.2, as shown in
After all, in order to mix the injected fuel and air by the vortex air flow u, thereby promoting the uniformization of the fuel gas, and ensure a sufficient space for the internal structure, thereby controlling the flow, it is advisable to set the aspect ratio h/c at 0.2 to 0.75.
In the present embodiment, moreover, the vane thickness of the swirl vane 130 is set at 0.1 to 0.3 times the vane chord length c of the swirl vane 130. By so doing, the pressure loss can be decreased, with ample fuel passages being ensured within the vane.
If the vane thickness of the swirl vane 130 is smaller than a length which is 0.1 times the vane chord length c of the swirl vane 130, adequate fuel passages cannot be secured within the swirl vane 130. Thus, a pressure loss for fuel supply is increased, and the amount of fuel blowoff becomes nonuniform.
Conversely, if the vane thickness of the swirl vane 130 is larger than a length which is 0.3 times the vane chord length c of the swirl vane 130, the vane surface boundary layer of the swirl vane 130 thickens, causing a great pressure loss of air. Depending on conditions, the air flow separates from the vane surface.
Furthermore, according to the present embodiment, the thickness of the vane at the rear edge of the swirl vane 130 is rendered smaller than a length which is 0.2 times the throat length.
As noted above, the thickness of the vane at the rear edge of the swirl vane 130 is rendered small, thus resulting in a thin shallow wake. Hence, the occurrence of flashback can be prevented.
In the above-described Embodiment 1, the swirl vane 130 is configured, as shown in
In Embodiment 2, there is adopted the swirl vane 130 configured, as shown in
The swirl vanes 130, in each of which the angle formed by the tangent to the average camber line of the swirl vane 130 at the rear edge of the swirl vane 130 and the axis line extending along the axial direction of the fuel nozzle 110 is rendered the same for the inner peripheral side and the outer peripheral side of the rear edge of the swirl vane 130, are provided on the outer peripheral surface of the fuel nozzle 110, and this composite is assembled to the interior of the burner tube 120 in the same mode as that in
Other features are the same as those in Embodiment 1, and the same effects as those in Embodiment 1 can be obtained.
That is, in Embodiment 2 as well,
the ratio between the vane height of the swirl vane 130 and the length of the clearance (clearance length/vane height) is set at 1 to 10%,
the clearance setting rib 131, which makes intimate contact with the inner peripheral surface of the burner tube 120, is provided at a portion of the outer peripheral side end surface of the swirl vane 130,
the aspect ratio between the vane chord length and the vane height of the swirl vane 130 (vane height/vane chord length) is set at 0.2 to 0.75,
the vane thickness of the swirl vane 130 is set to be a length which is 0.1 to 0.3 times the vane chord length of the swirl vane 130,
the vane thickness at the rear edge of the swirl vane 130 is smaller than 0.2 times the throat length, and
the injection holes 133a and the injection holes 133b can be formed at displaced positions in the swirl vane 130.
The features of Embodiment 2 are the same as the features of Embodiment 1, except that the angle formed by the tangent to the average camber line of the swirl vane 130 at the rear edge of the swirl vane 130 and the axis line extending along the axial direction of the fuel nozzle 110 is rendered the same for the inner peripheral side and the outer peripheral side of the rear edge of the swirl vane 130. These same features and portions as those in Embodiment 1 can obtain the same effects as those in Embodiment 1.
| Number | Date | Country | Kind |
|---|---|---|---|
| 2005-165189 | Jun 2005 | JP | national |
| Filing Document | Filing Date | Country | Kind | 371c Date |
|---|---|---|---|---|
| PCT/JP2006/311108 | 6/2/2006 | WO | 00 | 4/27/2007 |
| Publishing Document | Publishing Date | Country | Kind |
|---|---|---|---|
| WO2006/132153 | 12/14/2006 | WO | A |
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