Patent Grant
7694521
The present invention relates to a combustor which is provided to a gas turbine and the like, and especially, relates to a combustor which is provided with a pilot nozzle diffusing a fuel to burn and with main nozzles mixing a fuel with the air to burn.
In recent years, in order to reduce air pollution, at electric generation facilities utilizing gas turbines, it is demanded to reduce NOx which is included in exhaust gas thereof. NOx in a gas turbine is generated in a combustor which performs combustion behavior in order to rotate the gas turbine. Therefore, conventionally, in order to reduce NOx being generated in a combustor, is employed a combustor having main nozzles which perform combustion (premixed combustion) by mixing the fuel with the air.
By having the main nozzles perform premixed combustion, it is possible to reduce the amount of NOx being exhausted from the combustor. However, combustion state thereof is unstable, and combustion vibrations occur. Therefore, in order to restrain the aforementioned combustion vibrations so as to make the combustion state stable, such a combustor is employed as is further equipped with a pilot nozzle which diffuses and burns the fuel (diffusion combustion).
As shown in
In a combustor being constructed as mentioned hereinabove, the surrounding area of the tip portion of the pilot nozzle 2 is constructed as shown in
Additionally, the fuel being injected from the main nozzles 3 (“main fuel”) flows into the main burners 5 together with the air (“main air”), passing through the main swirls 7 and is mixed inside the main burners 5, thereby letting the main fuel and the main air being mixed by the main burners 5 flow out. When an air-fuel pre-mixture which is a mixture of the main air and the main fuel flows out from the main burners 5, the air-fuel pre-mixture is burned toward the inner wall of the combustor main body 1 from the downstream-side tips of the main burners 5, based on combustion in the low-speed flame-stabilizing zone “X.” Herein, “downstream” means the downstream of the fuel and the air flows.
Moreover, as a conventional technology, in order to have a low-speed flame-stabilizing zone “X” formed easily in order to maintain combustion of the air-fuel pre-mixture from the main burners 5, as shown in
However, in a combustor being provided with a pilot nozzle 2 and main nozzles 3 as shown in
Consequently, NOx emission from a combustor is reduced by decreasing the ratio of the fuel being provided to the pilot nozzle versus the entire fuel being provided to the combustor (“pilot ratio”). However, as mentioned hereinabove, when the pilot ratio is low, the flame-stabilizing effect cannot be obtained from the pilot nozzle 2. As a result, combustion vibrations occur, making the combustion state unstable, thereby deteriorating energy efficiency of a gas turbine.
Additionally, stability of combustion can be achieved by forming a low-speed flame-stabilizing zone “X” as shown in
It is an object of the present invention to provide a combustor, wherein the pilot ratio is low and combustion vibrations are restrained. Additionally, it is another object of the present invention is to provide a combustor, wherein the low-speed flame-stabilizing area can be made larger and more reliable as well as the stagnant area can be prevented from being generated at the outlets of the main burners.
In order to achieve the above-mentioned objects, a combustor in accordance with the present invention is characterized by including: a pilot puzzle which is installed in the center portion of the combustor main body; a plurality of main nozzles which are installed around the circumference of the pilot nozzle, being equally spaced; a pilot cone which covers the downstream-side tip portion where the fuel of the pilot nozzle flows and which has the tip portion thereof provided with a tapered portion of the inner circumference of a cone that is shaped to be tapered in a radial pattern toward the downstream side; and pilot swirls which are installed so as to be in contact with the inner wall surface of the pilot cone and to support the pilot nozzle in the center portion of the pilot cone, wherein the fuel is injected therein from the fuel injection ports being provided to the outer circumference of the pilot nozzle tip to inject the fuel bump against the inner wall surface of the tapered portion of the inner circumference of a cone from the position being half as long as the tapered portion of the inner circumference of a cone to the downstream-side tip.
Additionally, the combustor in accordance with the present invention is characterized by including: a pilot puzzle which is installed in the center portion of the combustor main body; a plurality of main nozzles which are installed around the circumference of the pilot nozzle, being equally spaced; a pilot cone which covers the downstream-side tip portion where the fuel of the pilot nozzle flows and which has the tip portion thereof provided with a tapered portion of the inner circumference of a cone that is shaped to be tapered in a radial pattern toward the downstream side; and pilot swirls which are installed so as to be in contact with the inner wall surface of the pilot cone and to support the pilot nozzle in the center portion of the pilot cone; and is characterized by that when the opening angle of the pilot cone is “θ,” the injection angle of the fuel being injected from the fuel injection ports being provided to the outer circumference of the tip of the pilot nozzle so as to inject the fuel is “θ/2,” wherein, the fuel is injected in parallel with the inclination of the tapered portion of the inner circumference of a cone.
Moreover, the combustor in accordance with the present invention is characterized by including: a pilot nozzle which is installed in the center portion of the combustor main body; a plurality of main nozzles which are installed around the circumference of the pilot nozzle, being equally spaced; a pilot cone which covers the downstream-side tip portion where the fuel of the pilot nozzle flows; and pilot swirls which are installed so as to be in contact with the inner wall surface of the pilot cone and to support the pilot nozzle in the center portion of the pilot cone. The combustor is characterized by including: a first fuel supply channel having a large part of the fuel being installed in the center portion of the pilot nozzle and being supplied to the pilot nozzle pass through; a second fuel supply channel being installed around the first fuel supply channel and having the remaining fuel being supplied to the pilot nozzle pass through; a cylindrical pilot nozzle cover whose outer wall surface is in contact with the inner wall surface of the pilot swirls, covering the downstream-side tip of the pilot nozzle and leading the air passing through the outer circumference of the pilot nozzle to the downstream-side tip of the pilot nozzle; a first fuel injection pipe being installed to the outer circumference of the downstream-side tip of the pilot nozzle, penetrating through the pilot nozzle cover from the first fuel supply channel and injecting the fuel being supplied from the first fuel supply channel to the outer circumference of the pilot nozzle cover; and fuel injection ports being provided to the upstream side to the first fuel injection pipe on the outer circumference of the pilot nozzle, being connected to the second fuel supply channel, and injecting the fuel being supplied from the second fuel supply channel to the region, consisting of the pilot nozzle cover and the pilot nozzle.
In addition, the combustor in accordance with the present invention is characterized by including: a pilot puzzle which is installed in the center portion of the combustor main body; a plurality of main nozzles which are installed around the circumference of the pilot nozzle, being equally spaced; a pilot cone which covers the downstream-side tip portion where the fuel of the pilot nozzle flows; pilot swirls which are installed so as to be in contact with the inner wall surface of the pilot cone and to support the pilot nozzle in the center portion of the pilot cone; and a cylinder which is in contact with the downstream-side surfaces of the pilot swirls and comes close to the outer wall surface of the pilot nozzle being located downstream side to the pilot swirls and has a tip portion thereof equipped with a collar being tapered so as to be formed in a radial pattern toward the downstream side.
Furthermore, the combustor in accordance with the present invention is characterized by including: a pilot puzzle which is installed in the center portion of the combustor main body; and a bypass pipe which is connected to a bypass valve bypassing the air being not used for combustion to the downstream side of the combustor and which is installed to the upper side of the combustor main body. Wherein, the pilot nozzle has a plurality of fuel injection ports which is installed at the positions excluding the nearest position to the bypass pipe in order to inject the fuel being supplied to the pilot nozzle and which is installed to the outer circumference of the downstream-side tip thereof.
Additionally, the combustor in accordance with the present invention is characterized by including: a pilot puzzle which is installed in the center portion of the combustor main body; and a connection pipe which is installed to the side surface of the combustor main body, propagating the flame to another combustor. Wherein, the pilot nozzle has a plurality of fuel injection ports which is installed at the positions excluding the nearest position to the connection pipe in order to inject the fuel being supplied to the pilot nozzle which is installed to the outer circumference of the downstream-side tip thereof.
Also, the combustor in accordance with the present invention is characterized by including: a pilot puzzle which is installed in the center portion of the combustor main body; and a bypass pipe which is connected to a bypass valve bypassing the air being not used for combustion to the downstream side of the combustor and which is installed to the upper side of the combustor main body. Wherein, the bypass valve is slightly opened in the state of combustion.
Additionally, the combustor in accordance with the present invention is characterized by including: a pilot puzzle which is installed in the center portion of the combustor main body; a plurality of main nozzles which are installed around the circumference of the pilot nozzle, being equally spaced; a pilot cone which covers the downstream-side tip portion where the fuel of the pilot nozzle flows; and main burners which cover the downstream-side tips of the main nozzles. Wherein, the pilot cone comprises: a tapered portion of inner circumference of a cone being formed in a tapered shape so as to stretch out in a radial pattern toward a downstream side; and a collar portion which is provided to an external periphery of a downstream-side tip of the tapered portion of inner circumference of a cone and serves as a surface being approximately vertical to axial direction of the said pilot nozzle. Wherein, an angle in axial direction to a line connecting an external periphery of a downstream-side tip of the pilot nozzle and an external periphery of downstream-side tips of the main burners is specified as “αx,” an opening angle of the tapered portion of inner circumference of a cone “θ” is “0≦θ<2 αx.”
Moreover, the combustor in accordance with the present invention is characterized by including: a pilot puzzle which is installed in the center portion of the combustor main body; a plurality of main nozzles which are installed around the circumference of the pilot nozzle, being equally spaced; a pilot cone which covers the downstream-side tip portion where the fuel of the pilot nozzle flows; and main burners which cover the downstream-side tips of the main nozzles. Wherein, the pilot cone comprises: a tapered portion of inner circumference of a cone being provided to downstream-side tip portion and being formed to be tapered, extending in a radial pattern to proximity of downstream-side tips of the main burners, a first cylindrical portion protruding from an external periphery of downstream-side tip of the tapered portion of inner circumference of a cone to centers of the main burners; a second cylindrical portion protruding from an external periphery of downstream-side tip of the tapered portion of inner circumference of a cone to centers of the main burners: and a cylinder being formed so as to be along an outer wall of the tapered portion of inner circumference of a cone and have downstream-side tip thereof be in contact with downstream-side tips of the main burners.
Furthermore, the combustor in accordance with the present invention is characterized by including: a pilot puzzle which is installed in the center portion of the combustor main body; a plurality of main nozzles which are installed around the circumference of the pilot nozzle, being equally spaced; a pilot cone which covers the downstream-side tip portion where the fuel of the pilot nozzle flows; and main burners which cover the downstream-side tips of the main nozzles. Wherein the pilot cone is installed to the downstream-side tip portion, and is also characterized by including: a first cylindrical portion which protrudes in the direction of the center of the main burners from the tapered portion of the inner circumference of the tapered cone spreading in a radial pattern close to the downstream-side tips of the main burners and from the outer edge of the downstream-side tip of the tapered portion of the inner circumference of a cone; a second cylindrical portion which protrudes in the direction of the center of the pilot burner from the outer edge of the downstream-side tip of the tapered portion of the inner circumference of a cone; and a cylinder being formed so as to be along the outer wall of the tapered portion of the inner circumference of a cone and having the downstream-side tip thereof get in contact with the downstream-side tips of the main burners.
Referring now to the drawings, a combustor of the present invention will be described hereinafter. In each embodiment to be described hereinafter, outline of the relationship of each of portions constituting a combustor is expressed by a schematic block diagram of
A first embodiment of the present invention will be described by referring to a figure.
A combustor of
Constructed as mentioned hereinabove, the pilot cone 4 is formed so as to be tapered, spreading in a radial pattern toward the downstream-side tip thereof (The portion which spreads in a radial pattern will be referred as a “tapered portion of the inner circumference of a cone” hereinafter.) By having the tapered portion of the inner circumference of a cone 41 shaped so as to spread in a radial pattern, the pilot fuel being injected from the fuel injection ports 21 being installed to the outer circumference of the tip of the pilot nozzle 2 and the pilot air flowing through the pilot swirls 6 are introduced to a low-speed flame-stabilizing zone “X” serving as the periphery of the tapered portion of the inner circumference of a cone 41, being located in the proximity of the downstream-side tips of the main burners 5.
Additionally, when the opening angle of the tapered portion of the inner circumference of a cone 41 is “θ,” the spray angle “α” of the pilot fuel being injected from the fuel injection ports 21 is specified to be −90°≦α<−θ/2 and θ/2<α≦90°. By specifying as mentioned hereinabove, in case of “−90°≦α<θ/2,” the fuel bumps, on the side opposite to where the respective fuel injection port 21 are located with respect to the center of the pilot nozzle 2, against the inner wall of the tapered portion of the inner circumference of a cone 41; and in case of “θ/2<α≦90°,” the fuel hits against the inner wall of the tapered portion of the inner circumference of a cone 41 which is close to the portion where the respective fuel injection ports 21 are located.
Furthermore, the length “a” along the inner wall surface of the tapered portion of the inner circumference of a cone 41 from the position “y” where the pilot fuel bumps against the inner wall of the tapered portion of the inner circumference of a cone 41 to the downstream-side tip of the pilot cone 4 satisfies the relation of “0<a≦A/2” for the length “A” along the entire inner wall surface of the tapered portion of the inner circumference of a cone 41. To put it plainly, the spray angle “α” and the position of the downstream-side tip of the pilot nozzle 2 are determined in a manner that the bumping position “y” of the pilot fuel on the inner wall of the tapered portion of the inner circumference of a cone 41 will be located within the range from the center of the tapered portion of the inner circumference of a cone 41 to the downstream-side tip thereof. At this time, the pilot nozzle 2 is installed so as to have the position of the tip of the pilot nozzle 2 located within the range between the downstream-side tip of the pilot cone 4 and the downstream-side surfaces of the pilot swirls 6.
As described hereinabove, because the pilot fuel bumps between the center of the pilot cone 4 and the downstream side, the pilot fuel burns from the bumping position “y” along the tapered shape of the tapered portion of the inner circumference of a cone 41 of the pilot cone 4. Therefore, it becomes easy for the pilot flame to be introduced to the low-speed flame-stabilizing zone “X.” In consequence, although the pilot fuel is reduced, it is possible to enhance flame stability in the low-speed flame-stabilizing zone “X.”
Based on the above, because the air-fuel pre-mixture having the main fuel being injected from the main nozzle 3 mixed in the main burners 5 with the main air passing through the main swirls 7 burns stably with the low-speed flame-stabilizing zone “X” serving as the flame-stabilizing point, it is possible to burn the air-fuel pre-mixture stably. Therefore, because it is possible to restrain combustion vibrations from occurring when the air-fuel pre-mixture is burned, combustion vibrations can be restrained by stabilizing combustion in a combustor although the pilot ratio is lowered by decreasing the pilot fuel.
Additionally, the closer to the downstream-side tip of the pilot cone 4 the bumping position “y” of the pilot fuel is, the more pilot fuel reaches the low-speed zone flame-stabilizing “X,” so that the flame stability in the low-speed flame-stabilizing zone “X” will be improved. Consequently, in the above-mentioned region, combustion vibrations in a combustor can be restrained when the pilot ratio is small, by specifying the position of the downstream-side tip of the pilot nozzle 2 and the spray angle of the pilot fuel so as to make the bumping position “y” of the pilot fuel come close to the downstream-side tip of the pilot cone 4.
A second embodiment of the present invention will be described by referring to figures.
Being different from the combustor in
Additionally, it is desirable to make the distance “c” between the injecting direction of the pilot fuel and the inner wall surface of the tapered portion of the inner circumference of a cone 41 be “½ (B−D),” where the diameter at the downstream-side tip of the pilot cone 4 is “B” and the diameter of the pilot nozzle 2 is “D.” Furthermore, it is more desirable to make the distance “c” be 20 mm or less. In addition, at this time, the pilot nozzle 2 is installed in such a manner as the position of the tip of the pilot nozzle 2 is located within the range between the downstream-side tip of the pilot cone 4 and the downstream-side surfaces of the pilot swirls 6.
As shown in
A third embodiment of the present invention will be described by referring to a figure.
A combustor in
Moreover, fuel injection pipes 21a that are installed to the outer circumference of the downstream-side tip of the pilot nozzle 2 and injects the pilot fuel being provided through the main fuel supply channel 22 are provided so as to penetrate through the pilot nozzle cover 9; and flame-stabilizing fuel injection ports 24 which inject the pilot fuel being supplied through the flame-stabilizing fuel channel 23 are installed to the outer wall surface of the pilot nozzle 2 on the more upstream side than the fuel injection pipes 21a. By making the fuel injection orifices 21 (
When the combustor is constructed as mentioned hereinabove, a part of the pilot air flowing on the side of outer circumference of the pilot nozzle 2 flows through a sweep air supply pathway 25 consisting of the pilot nozzle 2 and the pilot nozzle cover 9, serving as the sweep air which prevents the fuel injection pipes 21a from being burned, and a large part of the remaining pilot air passes through the pilot swirls 6. Additionally, the sweep air is mixed with the pilot fuel being injected from the flame-stabilizing fuel injection ports 24 and the air-fuel pre-mixture is discharged from the downstream-side tip of the sweep air supply pathway 25.
Here, the surrounding areas of the fuel injection pipes 21a are cooled by the air-fuel pre-mixture going through the sweep air supply pathway 25, thereby preventing the vicinity of the fuel injection pipes 21a from being burned. In order to prevent the vicinity of the fuel injection pipes 21a from being burned as mentioned hereinabove, the flow volume of the pilot fuel flowing through the flame-stabilizing fuel supply channel 23 is set so that the pilot fuel will be dilute in density, wherein the combustion gas temperature of the air-fuel pre-mixture is 1500° C. or less. When the air-fuel pre-mixture obtains such density as the combustion gas temperature is higher than 1500° C., there is a concern of occurrence of flashback. In addition, the pilot fuel flowing through the main fuel supply channel 22 is injected to the outside of the pilot nozzle cover 9 from the fuel injection pipes 21a.
Because the air-fuel pre-mixture is discharged from the downstream-side tip of the sweep air supply pathway 25 when the pilot fuel being injected from the fuel injection pipes 21a is diffused and burned, it is possible to enhance flame stability of the pilot diffusion flame by the pilot fuel from the fuel injection pipes 21a. Therefore, because the flame stability of the air-fuel pre-mixture being mixed by the main burners 5 and burned by the pilot diffusion flame can also be enhanced, it is possible to restrain the combustion vibrations by making combustion in a combustor stable although the pilot ratio is lowered.
A fourth embodiment of the present invention will be described by referring to a figure.
Being different from the combustor in accordance with the third embodiment (
By installing the pilot nozzle covers 9a and 9b as mentioned hereinabove, the sweep air flows through the sweep air supply pathway 25 consisting of the pilot nozzle 2 and the pilot nozzle cover 9b and is mixed with the pilot fuel being injected from the flame-stabilizing fuel injection ports 24. The air-fuel pre-mixture being a mixture of the pilot fuel and the sweep air flows into the air-fuel pre-mixture supply pathway 25a consisting of the pilot nozzle 2 and the pilot nozzle cover 9a and into the air-fuel pre-mixture supply pathway 25b consisting of the pilot nozzle covers 9a and 9b, respectively.
Then, the air-fuel pre-mixture flowing through the air-fuel pre-mixture pathway 25b to be discharged is discharged to downstream side of the fuel injection pipes 21a, and the air-fuel pre-mixture flowing through the air-fuel pre-mixture supply pathway 25b to be discharged is discharged to the upstream side of the fuel injection pipes 21a. Therefore, because the pilot fuel being injected from the fuel injection pipes 21a can be wrapped by the air-fuel pre-mixture, the air-fuel pre-mixture can be supplied so as to wrap up the pilot diffusion flame, thereby enhancing the flame stability of the pilot diffusion flame.
A fifth embodiment of the present invention will be described by referring to a figure.
Being different from the combustor in accordance with the fourth embodiment (
By installing the flame-stabilizing fuel injection pipe 24a as mentioned hereinabove, the sweep air being supplied from the sweep air supply pathway 25 and flowing through the sweep air supply pathway 25c is discharged to the downstream-side tip of the pilot nozzle 2 without being mixed with the pilot fuel. Consequently, it is ensured that the downstream-side tip of the pilot nozzle 2 is cooled by the sweep air.
Moreover, the sweep air flowing into the air-fuel pre-mixture supply pathway 25b consisting of the pilot nozzle covers 9a and 9b is mixed with the pilot fuel being injected from the flame-stabilizing fuel injection pipe 24a and discharged to the upstream side of the fuel injection pipe 21a as an air-fuel pre-mixture. Consequently, because the air-fuel pre-mixture is supplied to the surrounding area of the pilot diffusion flame, the flame stability of the pilot diffusion flame can be enhanced.
In addition, in the third through the fifth embodiments of the present invention, such a combustor may be applied, wherein the relation between the spray angle of the pilot fuel being injected from the fuel injection pipe 21a and the tapered portion of the inner circumference of a cone 41 of the pilot cone 4 is such as the relation in the first or the second embodiment.
A sixth embodiment of the present invention will be described by referring to a figure.
The combustor in
Additionally, the collar 101 of the cylinder 10 is so constructed as not to interfere with the jet flow of the pilot fuel being injected from the fuel injection ports 21. In order to be constructed so as to prevent interference with the jet flow of the pilot fuel as mentioned hereinabove, for example, as shown in
In addition, for example, as shown in
Because vortex of the pilot fuel is formed in the vicinity “Z” at the tip portion of the collar 101 when the pilot fuel flows along the collar 101 of the cylinder 10 due to construction as mentioned hereinabove, a circulation area serving as a low-speed zone is formed. Consequently, because the pilot fuel does not hit against the base of the jet flow of the pilot fuel in the surrounding area of the fuel injection ports 21, it is possible to prevent the pilot diffusion flame from weakening; and in addition, because a circulation area is formed in the vicinity “Z” of the tip portion of the collar 101, the pilot diffusion flame can be burned stably.
A seventh embodiment of the present invention will be described by referring to a figure.
Same as the combustor in accordance with the sixth embodiment (
Moreover, the collar 102 is formed at the position drifting slightly toward the upstream side from the downstream-side tip of the pilot nozzle 2, wherein the opening angle “γ” of the collar 102 is specified to be “0°<γ<2α.” Then, by setting the length “s” of the collar 102 so as to satisfy “s≧t/(cos(γ/2)−tanα×sin(γ/2)),” the pilot fuel being injected from the fuel injection ports 21 is made to hit against the collar 102. Additionally, in order that the pilot air can pass sufficiently between the pilot cone 4 and the cylinder 10a, the distance “1” between the inner wall surface of the pilot cone 4 and the collar 102 at the position of the downstream-side tip of the cylinder 10a is specified to be “0<1≦k,” or more preferably, to be” 1≧/2.”
Being constructed as mentioned hereinabove, a low-speed zone is formed by a hitting point where the pilot fuel bumps in the collar 102 of the cylinder 10a, thereby burning the pilot fuel along the collar 102. Therefore, because the pilot air does not hit against the base of the jet flow of the pilot fuel and against the hitting point of the pilot fuel in the surrounding area of the fuel injection ports 21, the pilot diffusion flame can be prevented from weakening as well as the stability of the pilot diffusion flame is enhanced at the hitting point by the collar 102, thereby burning the pilot diffusion flame stably.
In addition, in the sixth and the seventh embodiments of the present invention, such a combustor may be applied, wherein the relation between the spray angle of the pilot fuel being injected from the pilot injection ports 21 and the tapered portion of the inner circumference of a cone 41 is such as the relation in the first or the second embodiment. Moreover, as the third through the fifth embodiments, the pilot nozzle covers 9, 9a and 9b may be installed, covering the downstream-side tip of the pilot nozzle 2.
An eighth embodiment of the present invention will be described by referring to figures.
In the combustor in
Because the combustor body 150 is provided with the air bypass pipe 151 and the connection pipe 152 that serve as hollows, the hollow being made by each of the air bypass pipe 151 and the connection pipe 152 serves as a stagnant area of the fuel gas, respectively, when combustion is performed by the combustor. Therefore, in the areas in the proximity of the air bypass pipe 151 and the connection pipe 152, combustion becomes unstable, which in consequence, causes combustion vibrations to occur and affects combustion in other areas.
Consequently, as shown in
In addition, in a similar manner to the aforesaid, for another example as shown in
By plugging the fuel injection ports 21 being located to the hollows being made by the air bypass pipe 151 or the connection pipe 152, it is possible to prevent the fuel gas from diffusing to the hollows being made by the air bypass pipe 151 or the connection pipe 152. As a result, stagnation of the fuel gas due to the hollows by the air bypass pipe 151 or the connection pipe 152 can be prevented, thereby restraining combustion vibrations when the pilot ratio is lowered.
Additionally, as shown in
Furthermore, in the combustor in accordance with this embodiment, the surrounding area of the pilot nozzle thereof may be constructed in such a manner as the first through the seventh embodiments are constructed. Wherein, the surrounding area of the pilot nozzle may have such a construction as the characteristics being described for the first through the seventh embodiments are combined.
A ninth embodiment of the present invention will be described by referring to a figure.
The combustor in
Being constructed as described hereinabove, the pilot cone 4a has a tapered form so as to spread out toward the downstream-side tip in a radial pattern. (The portion spreading out in the radial pattern is referred as the “tapered portion of the inner circumference of a cone” hereinafter.) Then, the outer circumference of the downstream-side tip of the tapered portion of the inner circumference of a cone 41 has a collar 42 installed thereto, serving as an approximately vertical surface against the axial direction of the pilot nozzle 2. The collar 42 is formed in a ring spreading from the downstream-side tip of the tapered portion of the inner circumference of a cone 41 toward the downstream-side tips of the main burners 5. Additionally, the collar 42 is installed so as to be located on the downstream side for about several millimeters from the downstream-side tips of the main burners 5.
In addition, the pilot cone 4a has a tapered cylinder 43 spreading toward the downstream side in a radial pattern installed to the outer circumference of the tapered portion of the inner circumference of a cone 41. Same as the tapered portion of the inner circumference of a cone 41, the cylinder 43 has the downstream-side tip thereof provided with a ring collar 44 serving as an approximately vertical surface against the axial direction of the pilot nozzle 2 so as to confront the collar 42. Additionally, the collar 44 is installed to the position of the downstream-side tips of the main burners 5. Then, the cylinder 43 is installed so as to have a space formed between the cylinder 43 and the tapered portion of the inner circumference of a cone 41. Wherein, a space is also made between the collar 42 of the tapered portion of the inner circumference of a cone 41 and the collar 44 of the cylinder 43.
By forming the pilot cone 41 so as to spread in a radial pattern as described hereinabove, the pilot fuel being injected from the fuel injection ports 21 which are provided to the outer circumference of the tip of the pilot nozzle 2 is diffused and burned by the pilot air passing through the pilot swirls 6 and introduced to the downstream-side tips of the main burners 5. Then, the pilot diffusion flame is led to the flame-stabilizing low-speed zone “X” being formed on the downstream side of the collar 42 of the tapered portion of the inner circumference of a cone 41, along the inner wall of the tapered portion of the inner circumference of a cone 41. The flame-stabilizing low-speed zone “X” is sized in accordance with the width “1” of the collar 42 of the tapered portion of the inner circumference of a cone 41.
Moreover, in flowing into the space between the tapered portion of the inner circumference of a cone 41 and the cylinder 43, the air passing through the outer circumference of the pilot cone 4a flows out to the downstream-side tips of the main burners 5, passing through the space between the collar 42 and the collar 44, and flows into the portion serving as the boundary between the main burners 5 and the pilot cone 4a, being in a form of film. By flowing the air in film to the boundary in the above-mentioned manner, flashback being caused by the flame in the flame-stabilizing low-speed zone “X” can be prevented. Additionally, because the air passes through the space between the tapered portion of the inner circumference of a cone 41 and the cylinder 43, the tapered portion of the inner circumference of a cone 41 and the collar 42 can be cooled.
By having the flame-stabilizing low-speed zone “X” formed by the collar 42 of the tapered portion of the inner circumference of a cone 41, where the angle being formed by the line connecting the periphery of the downstream-side tip of the pilot nozzle 2 to the periphery of the downstream-side tips of the main burners 5 at the nearest point thereof and the axial direction of the pilot nozzle 2 is “αx,” the opening angle “θ” of the tapered portion of the inner circumference of the main cone 41 is specified to be “0°<θ<2α x.” Wherein, it is preferable that the opening angle “θ” is 60° or less, and more preferable, narrower than the angle of “37°±3°.”
In consequence, because the width “1” of the collar 42 being formed inside the area connecting the main burners 5 respectively can be sufficiently wide and the area thereof can be made sufficiently large, the size of the flame-stabilizing low-speed zone “X” being formed on the downstream side of the collar 42 can be made sufficiently large, thereby enhancing the flame stability. Additionally, because the collar 42 does not protrude from the downstream-side tips of the main burners 5, no stagnant areas are formed at the downstream-side tips of the main burners 5, thereby preventing flashback from occurring.
A tenth embodiment of the present invention will be described by referring to a figure.
Being different from the combustor in accordance with the ninth embodiment (
Same as the ninth embodiment, the cylinder 43 has a collar 44 installed to the downstream-side tip thereof, and the cylinder 45 has a collar 46 installed to the upstream-side tip thereof so as to confront the collar 44. Same as the ninth embodiment, the collar 44 is formed in a ring so as to spread from the downstream-side tip of the cylinder 43 toward the downstream-side tips of the main burners 5, and the collar 46 is formed in a ring so as to spread from the upstream-side tip of the cylinder 45 toward the downstream-side tips of the main burners 5. The cylinder 45 being provided with the collar 46 is installed in a manner that the downstream-side tip thereof corresponds to the downstream-side tip of the tapered portion f the inner circumference of a cone 41b.
Additionally, the cylinders 43 and 45 are installed so as to have spaces provided between the tapered portion of the inner circumference of a cone 41b and the cylinder 43, between the tapered portion of the inner circumference of a cone 41b and the cylinder 45, and between the collar 44 and the collar 46. As a result, because the collar 44 of the cylinder 43 is installed at the position of the downstream-side tips of the main burners 5, the collar 46 of the cylinder 45 is installed at the position drifting for several millimeters toward the downstream side from the downstream-side tips of the main burners 5.
Moreover, in the cylinder 45, it is preferable that the length “L” along the tapered portion of the inner circumference of a cone 41b is one through three times as much as the width “lx” of the collar 44 or the collar 46. Constructed as mentioned hereinabove, the pilot air flowing along the inner wall of the pilot cone 4b after passing through the pilot swirls 6 flows into the flame-stabilizing low-speed zone “X” being formed on the outer circumference of the cylinder 45, which can decrease the temperature of the flame-stabilizing low-speed zone as well as prevent the fuel density from being diluted.
In addition, by flowing the air from the space between the collar 44 and the collar 46, being in the form of film, flashback to the downstream-side tips of the main burners 5 can be prevented; and by flowing the air from the space between the tapered portion of the inner circumference of a cone 41b and the cylinder 45, being in the form of film, it is further ensured that the pilot air can be prevented from flowing into the flame-stabilizing low-speed zone “X.” Moreover, it is preferable that the opening angle “θ” of the tapered portion of the inner circumference of a cone 41b is specified to be “0 °≦θ<2αx” in the same manner as the first embodiment, so as to be 60° or less. It is more preferable that the opening angle “θ” is narrower than the angle of “37±3°.”
An eleventh embodiment of the present invention will be described by referring to figures.
Being different from the combustor in accordance with the ninth embodiment (
Then, the downstream-side tip of the tapered portion of the inner circumference of a cone 41c has a collar 42 installed thereto, serving as a vertical surface against the axial direction of the pilot nozzle 2; and at the same time, the outer edge of the collar 42 has a cylinder 47 installed thereto, being tapered so as to be adjacent to the main burners 5. To put it plainly, the diameter of the section which joins to the collar 42 of the tapered portion of the inner circumference of a cone 41c coincides with the diameter of the inner edge of the collar 42, and the diameter of the upstream-side tip of the cylinder 47 coincides with the diameter of the outer edge of the collar 44.
Additionally, same as the ninth embodiment, the pilot cone 4c has a cylinder 43c, which has a collar 44 provided to the position confronting to the collar 42, installed to the outer circumference of the tapered portion of the inner circumference of a cone 41c. Then, the cylinder 43c also has a cylinder 48 installed thereto, being tapered so as to be along the cylinder 47 on the outer edge of the collar 44. To put it plainly, the diameter of the section which joins to the collar 44 of the cylinder 43c coincides with the diameter of the inner edge of the collar 44, and the diameter of the upstream-side tip of the cylinder 48 coincides with the diameter of the outer edge of the collar 44. By installing a cylinder 43c between the main burners 5 and the tapered portion of the inner circumference of a cone 41c as mentioned hereinabove, it is possible to have the air passing through the outer circumference of the pilot cone 4c flow through the gap between the tapered portion of the inner circumference of a cone 41c and the cylinder 43c.
Moreover, same as the ninth embodiment, the opening angle “θ” on the upstream side of the collar 42 of the tapered portion of the inner circumference of a cone 41c is specified to be “0°≦θ<2αx.” It is preferable that the opening angle “θ” is 60° or less, and more preferable, narrower than the angle of “37±3°.” As just described, the collar 42 can obtain sufficient width and sufficient large area thereof in the same manner as the ninth embodiment. Constructed as hereinabove, a flame-stabilizing low-speed zone “X” having a sufficient size is formed on the downstream side of the collar 42.
In addition, the air passing through the outer circumference of the pilot cone 4c flows into the space between the tapered portion of the inner circumference of a cone 41c and the cylinder 43c, and flows from the space between the cylinder 47 and the cylinder 48 to the boundary between the main burners 5 and the pilot cone 4a, being in the form of film. At this time, because the cylinders 47 and 48 are shaped so as to be along the tips of the main burners 5, it can be ensured that the air flows in parallel with the air-fuel pre-mixture flowing from the main burners 5 and that an air space in the form of film is formed. In consequence, the flame stability in the flame-stabilizing low-speed zone “X” can be maintained and resistance to the flashback can be enhanced.
Additionally, in the eleventh embodiment, as shown in
A twelfth embodiment of the present invention will be described by referring to a figure.
Being different from the combustor in accordance with the ninth embodiment (
Being constructed as described hereinabove, a stagnant area is completely formed in a hollow which is formed toward the upstream-side tip of the double cylinder 50, so that the low-speed flame-stabilizing zone “X” gets into the recess of the hollow of the double cylinder 50. Consequently, it is possible to make the low-speed flame-stabilizing zone “X” being formed in the vicinity of the opening of the double cylinder 50 larger by forming it into the recess of the hollow of the double cylinder 50, thereby enhancing the flame stability thereof.
In addition, a part of the air flowing through the outer circumference of the pilot cone 4d flows out from the downstream-side tip of the tapered portion of the inner circumference of a cone 41d, being in a form of film, after flowing into the space between the tapered portion of the inner circumference of a cone 41d and the cylinder 50a. Moreover, a part of the air flowing through the outer circumference of the pilot cone 4d flows out from the downstream-side tips of the main burners 5, being in a form of film, after flowing into the space between the cylinder 50b and the cylinder 51. As a result, resistance to a flashback to the main burners 5 is enhanced.
A thirteenth embodiment of the present invention will be described by referring to a figure.
Being different from the combustor in accordance with the ninth embodiment (
Then, the downstream-side tip of the pilot cone 4e is installed so as to be located on the downstream side of the downstream-side tips of the main burners 5 for several millimeters. Additionally, the opening angle “β” of the collar 52 is set so as to be wider than the opening angle “θ” of the tapered portion of the inner circumference of a cone 41e, and, the inner wall of the cylinder 53 faces inward against the axial direction. Here, it is preferable that the angle “67 ” being formed by the inner wall of the cylinder 53 and the axial direction of the pilot nozzle 2 is within the range of “0°≦δ≦60°.” Moreover, the length of the inner wall of the cylinder 53 is set to be approximately the same as the width “lx” of the collar 52.
By being constructed as described hereinabove, a low-speed flame-stabilizing zone “X” is formed in the neighborhood of an area being constructed by the collar 52 and the cylinder 53. Because at this time, the collar 52 and the cylinder 53 are connected with each other at the upstream-side tips thereof respectively, providing a hollow to the upstream side and being shaped so as to open to the downstream side, a stagnant area can be formed in a hollow to the joint portion of the collar 52 and the cylinder 53. Consequently, the low-speed flame-stabilizing zone “X” can be made larger and flame stability thereof can be enhanced.
Additionally, a part of the air flowing through the outer circumference of the pilot cone 4e flows out to the downstream-side tips of the main burners 5, being in a form of film, after flowing into the space between the tapered portion of the inner circumference of a cone 41e and the cylinder 43e. Because the downstream-side tip of the cylinder 43e is installed so as to come in contact with the downstream-side tips of the main burners 5, the air can surely be led to the downstream-side tips of the main burners 5, thereby preventing flashback to the to the main burners 5.
A fourteenth embodiment of the present invention will be described by referring to figures.
A combustor of
A same number of flame-stability-enhancing fuel supply channels 8 as that of the main nozzles 3 are installed in such a manner as the centers thereof are located on a line connecting the center of the pilot nozzle 2 to the centers of the main nozzles 3. (However, the same number of flame-stability-enhancing fuel supply channels 8 should not necessarily be installed as that of the main nozzles, but appropriate number may be installed.) Additionally, the flame-stability-enhancing fuel manifold 95 is installed upstream of the main fuel manifold 90, and the flame-stability-enhancing fuel supply channels 8 being connected to the flame-stability-enhancing fuel manifold 95 are inserted into a hole 91 being provided in the main fuel manifold 90. Moreover, the pilot nozzle 2 is inserted into holes 92 and 96 being made in the centers of the main fuel manifold 90 and flame-stability-enhancing fuel manifold 95, respectively.
In a combustor being constructed as described hereinabove, as shown in
By constructing as described hereinabove, a fuel being supplied from the flame-stability-enhancing fuel manifold 95 is injected to the low-speed flame-stabilizing zone “X” from the flame-stability-enhancing fuel injection ports 81 after passing through the flame-stability-enhancing fuel supply channels 8. By this, the fuel being injected from the flame-stability-enhancing fuel injection ports 81 burns in the low-speed flame-stabilizing zone “X,” thereby enhancing the flame stability in the low-speed flame-stabilizing zone “X.”
In addition, in the fourteenth embodiment, an example is given wherein flame-stabilizing-enhancing fuel supply channels 8 are installed to a combustor being provided with a pilot cone 4a in accordance with the ninth embodiment of the present invention, but may be installed to the combustor being provided with the pilot cones 4b through 4e in accordance with the tenth through the thirteenth embodiments. At this time, the pilot cone 4b has the flame-stability-enhancing fuel supply channels 8 provided so as to penetrate through the collars 44 and 46; the pilot cone 4c has the flame-stability-enhancing fuel supply channels 8 provided so as to penetrate through the collars 42 and 44; the pilot cone 4d has the flame-stability-enhancing fuel supply channels 8 so as to penetrate through the joint portion of the cylinders 50a and 50b; and the pilot cone 4e has the flame-stability-enhancing fuel supply channels 8 so as to penetrate through the joint portion of the collar 52 and the cylinder 53. By this, the fuel passing through the flame-stability-enhancing fuel supply channels 8 being provided respectively is injected to the low-speed flame-stabilizing zone “X.”
Moreover, the combustors in accordance with the ninth through the fourteenth embodiments may have the vicinity of the pilot nozzle thereof constructed in such a manner as the first through the eight embodiments. Here, the construction of the vicinity of the pilot nozzle thereof may be constructed so as to have a combination of characteristics that are described in the first through the eight embodiments.
As described above, in accordance with the present invention, it is possible to induce a large amount of fuel to a low-speed flame-stabilizing zone which is formed in the vicinity of the downstream-side tip of a pilot cone, by making the fuel being injected from the fuel injection ports bump against the proximity of the downstream-side tip of the pilot cone, which enhances the flame stability of pilot diffusion flames. Additionally, by injecting the fuel being injected from the fuel injection ports in parallel with the inner wall surface of the pilot cone, a large volume of fuel can be induced to the low-speed flame-stabilizing zone which is formed in the vicinity of the downstream-side tip of the pilot cone, thereby enhancing the flame stability of the pilot diffusion flames. Because by enhancing the flame stability of the pilot diffusion flames in the low-speed flame-stabilizing zone in a manner as mentioned hereinabove, combustion vibrations can be reduced, which can decrease the pilot ratio of the fuel being supplied to a combustor, thereby realizing the reduction of NOx.
Additionally, in accordance with the present invention, by injecting a fuel from the fuel injection ports to an area consisting of a pilot nozzle cover and a pilot nozzle and generating an air-fuel pre-mixture in which the fuel and the air are mixed so as to be supplied to the neighborhood of the pilot diffusion flames caused by the fuel being injected from the first fuel injection pipe, the flame stability of the pilot diffusion flames can be enhanced. Furthermore, because an air-fuel pre-mixture can be supplied so as to surround the pilot diffusion flames by having the pilot nozzle cover consist of the first cylinder cover and the second cylinder cover and generating air-fuel pre-mixture in the area between the pilot nozzle and the second cylinder cover and in the area between the first cylinder cover and the second cylinder cover, respectively, the flame stability of the pilot diffusion flames can be enhanced further. Moreover, by installing the second fuel injection pipe and generating the air-fuel pre-mixture only in the area between the first cylinder cover and the second cylinder cover, the downstream-side tip of the pilot nozzle can surely be cooled with the air passing through the area between the second cylinder cover and the pilot nozzle.
In addition, in accordance with the present invention, by providing a collar to the downstream-side tip of the cylinder being in contact with the downstream-side surface of the pilot swirl, the air passing through the outer circumference of the pilot nozzle is prevented from flowing to the downstream-side tip of the pilot nozzle, thereby enabling the air to flow into the base of the jet flow of the fuel being injected from the fuel injection ports. In consequence, combustion can be achieved without weakening the pilot diffusion flames.
Furthermore, by not installing the fuel injection ports to the position being close to the area having a hollow such as a bypass pipe, a connection pipe and the like at the downstream-side tip of the pilot nozzle, a stagnant area of a fuel can be prevented from being formed in the areas having a hollow such as a bypass pipe, a connection pipe and the like. Additionally, by slightly opening a bypass valve in the state of combustion, a stagnant area of a fuel can be prevented from being formed by a hollow of a bypass pipe. In consequence, instability of combustion in the stagnant area can be reduced.
In accordance with the present invention, because a collar portion is provided to the downstream-side tip of the pilot cone, a low-speed flame-stabilizing zone can be made large and surely be formed on the downstream side of the collar portion. In consequence, the flame stability of an air-fuel pre-mixture in which the fuel from the main burners and the air are mixed can be enhanced, thereby reducing the combustion vibrations. Additionally, because by providing a cylinder to the outer circumference of the tapered portion of the inner circumference of a cone, the air can be flowed in a form of a film from the downstream-side tips of the main burners, the collar portion for flame stabilizing can be cooled and the flashback to the main burners can be prevented.
Also, because by having the tapered portion of the inner circumference of a cone provided with a cylinder portion extending from the joint portion with the collar portion, the pilot air flows along the tapered portion of the inner circumference of a cone so as to be prevented from flowing into the low-speed flame-stabilizing zone, the flame stability in the low-speed flame-stabilizing zone can be enhanced. Moreover, because by providing a double cylinder to the outer circumference of the tapered portion of the inner circumference of a cone, a stagnant area can be formed in the hollow of the double cylinder, the flame stability can be enhanced by forming a low-speed flame-stabilizing zone into the recess of the hollow and making the size thereof large. Furthermore, the low-speed flame-stabilizing zone can surely be formed by the first and the second cylinders protruding to the main nozzles and the pilot nozzle, respectively, as well as the pilot air flowing along the tapered portion of the inner circumference of a cone can be prevented from flowing into the low-speed flame-stabilizing zone by the second cylinder.
Additionally, by providing a plurality of flame-stability-enhancing fuel supply channels so as to have the fuel pass between the pilot cone and the main burners, supply to the low-speed flame-stabilizing zone is possible through the flame-stability-enhancing fuel supply channels. In consequence, the flame stability in the low-speed flame-stabilizing zone can be enhanced.
| Filing Document | Filing Date | Country | Kind | 371c Date |
|---|---|---|---|---|
| PCT/JP2004/002666 | 3/3/2004 | WO | 00 | 12/22/2005 |
| Publishing Document | Publishing Date | Country | Kind |
|---|---|---|---|
| WO2005/085709 | 9/15/2005 | WO | A |
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| 20070006587 A1 | Jan 2007 | US |
