The present invention relates to a gas turbine combustor.
In the conventional gas turbine combustor, there is a case that defects such as thermal deformation is caused due to low cycle fatigue in the end portion (outlet) of the combustor tail pipe section during a burning operation. Since the thicknesses of structural plates are different between the side walls and the upper and lower walls in the end portion of the combustor tail pipe section so that the stiffness of the plate in the upper and lower walls thicker than the side walls is high, the low cycle fatigue is caused when thermal stress is impressed on the end portion of the combustor tail pipe section so that compulsory thermal deformation is caused in a plate of the side wall while a start and a stop of the operation of the gas turbine combustor are repeated. Therefore, while the gas turbine combustor repeats the start and the stop, the metal fatigue due to the thermal deformation is accumulated and a warp is generated in the plate of the side wall to form crack.
In conjunction with “Combustor and Gas Turbine” is disclosed in the Japanese Laid Open Patent Application (JP-P2004-84601A). In this conventional example, air compressed by a compressor and fuel are mixed and burned. Generated burning gas is introduced into a turbine through a burning pipe. In such a combustor, an air flow path is provided to extend along a surface of a sidewall section in the sidewall section for the burning pipe. An inlet of the air flow path is provided on a surface of the outer wall of the sidewall section. An outlet of the air flow path is provided for an end surface of the burning pipe.
Also, “Combustor and Gas Turbine” is disclosed in Japanese Laid Open Patent Application (JP-P2003-322337A). In this conventional example, air compressed by a compressor and fuel are mixed and burned. Generated burning gas is introduced into a turbine through a burning pipe. In such a combustor, reinforcement ribs are provided over whole width of a side surface of the burning pipe of an almost rectangular section.
Also, “Gas Turbine Combustor” is disclosed in Japanese Laid Open Patent Application (JP-P2003-193866A). In this conventional example, adjacent transition pieces (tail pipes) in neighborhood of the gas turbine combustor, and a transition piece and an initial stage still wing are engaged through the seal section. In such a gas turbine combustor, a seal section is made of cobalt alloy having a fatigue resistance coating layer, in which a film of carbide or nitride is formed as a lower layer and an alumina film is used as the uppermost surface film. A protection plate of cobalt alloy which contains chrome 15 to 35 weight % and carbon 0.7 to 1.5 weight % for a contact section of the transition piece with the seal section in the engaging portion.
Also, “Gas Turbine Combustor” is disclosed in Japanese Laid Open Patent Application (JP-P2003-185140A). In this conventional example, a combustor transition piece (tail pipe) and an initial stage stillness wing in the gas turbine for power generation are engaged through a seal section. In such a gas turbine combustor, cobalt alloy which contains chrome of 15 to 30 weight % and carbon of 0.05 to 0.25 weight % as a part of the chemical composition is used as a base member. A plate to which a coating of chrome carbide of 0.1 to 0.6 mm as a main component is carried out is used as a seal section. A cobalt alloy plate is attached to a contact section of the seal section with coating layer in the transition engaging portion.
An object of the present invention is to provide a gas turbine combustor in which it is possible to intentionally reduce the stiffness of flanges provided for upper and lower walls in a tail pipe section of the gas turbine combustor.
Another object of the present invention is to provide a gas turbine combustor in which deformation in an end portion of a tail pipe section can be suppressed and high stress generated in a side plate can be suppressed.
Another object of the present invention is to provide a gas turbine combustor in which fatigue resistance of the combustor is improved.
A gas turbine combustor of the present invention includes a combustor main body; a tail pipe connected with the combustor main body to spout out burning gas; and a seal section provided to prevent the burning gas from leaking from a space of a plurality of the tail pipes annularly arranged around one axis. The tail pipe has upper and lower walls opposite to each other in a radius direction of the axis in an end portion of the tail pipe, and a first engaging portion is provided for the upper and lower walls. The seal section has a second engaging portion for engagement with the first engaging portion in a front end of the seal section. The first engaging portion is provided to reduce stiffness of the upper and lower walls.
In the gas turbine combustor of the present invention, the tail pipe further includes side walls opposite to each other in a circumferential direction of the axis in the end portion of the tail pipe. The first engaging portion has a structure to reduce a stiffness of the upper and lower walls so as to be substantially equal to a stiffness of the side walls.
Also, in the gas turbine combustor of the present invention, the first engaging portion includes one set of flanges opposite to each other in the radius direction. In this case, the gas turbine combustor of the present invention may further include a shield plate provided along each of the flanges of the one set. The shield plate and the flange may be fixed by a shield plate fixing member, and the tail pipe and the seal section may be connected, by engaging each of the flanges of the one set in which the shield plate is provided, with the second engaging portion.
Also, in the gas turbine combustor of the present invention, the first engaging portion may include one set of flanges provided to oppose to each other in the radius direction and to extend in a flow direction of the burning gas. Each of the flanges and the second engaging portion may be engaged with each other in the flow direction of the burning gas. In this case, each of the flanges may have a convex section, and the second engaging portion may have a concave section which is engaged with the convex section to connect the tail pipe and the seal section.
Also, in the gas turbine combustor of the present invention, the tail pipe may further include a gusset provided on a position apart from the end portion of the tail pipe to extend in a perpendicular direction to a pipe surface of the tail pipe and to fix the tail pipe to a housing of the gas turbine. The gusset may have a first supporting section to engage the second engaging portion, the tail pipe may have a second supporting section provided on the pipe surface of the tail pipe opposite to the gusset to engage the second engaging portion. The tail pipe and the seal section may be connected by engaging the first and second supporting sections as the first engaging portion and the second engaging portion.
Also, in the gas turbine combustor of the present invention, the first engaging portion may include the one set of the flanges opposite to each other in the radius direction, and each of the flanges may have an opening. In this case, a seal plate may be provided along an external circumference of the opening. The external circumference and the seal plate may be welded, and the tail pipe and the seal section may be connected by engaging the one set of the flanges and the seal plate connected to the set and the second engaging portion.
Also, in the gas turbine combustor of the present invention, the first engaging portion may include one set of flanges opposite to each other in the circumferential direction, and each of the flanges may have a slit extending in a direction perpendicular to the flow direction of the burning gas.
A gas turbine of the present invention may include the gas turbine combustor according to any of the above.
Hereinafter, a gas turbine combustor of the present invention will be described in detail with the reference to the attached drawings.
In the gas turbine, a plurality of gas turbine combustors are annularly arranged around one axis. In order to prevent burning gas from leaking from each gas turbine combustor, a seal section is provided to cover an inner circumferential wall and an outer circumferential wall of an end section (outlet) of a tail pipe section of each of the combustors arranged annually (upper wall and lower wall in the gas turbine combustor). For this purpose, a flange is provided for each of the upper and lower walls of the end portion (outlet) of the tail pipe section of each combustor to attach the seal section.
In the gas turbine combustor of the present invention, the stiffness of the flange provided for each of the upper and lower walls of the end portion (outlet) of the tail pipe section is intentionally reduced such that the stiffness of the flange becomes substantially equal to the stiffness of a side plate of each of the side walls. Thus, compulsion deformation is suppressed which is caused due to thermal stress generated in the end portion (outlet) of the tail pipe section on the operation of the conventional gas turbine combustor, and it becomes possible to reduce high stress easy to generate in the side plate. As a result, the high fatigue resistance gas turbine combustor can be realized.
In the gas turbine combustor of the present invention, a plurality of gas turbine combustors are annularly arranged. A seal section is provided to cover each of the upper and lower walls of the end portion (outlet) of the tail pipe section of each combustor so that the burning gas from each combustor can be sealed. For this purpose, as
In the present embodiment, as shown in
In the gas turbine combustor according to the present embodiment, the height of each of the flanges which are provided for the upper and lower walls of the end portion (outlet) of the tail pipe section is reduced to a minimum height necessary for the flange and the seal section to engage and to carry out the positioning in a portion other than a positioning portion with the seal section. Thus, the stiffness of the flange in each of the upper and lower walls in the end portion (outlet) of the tail pipe section of the gas turbine combustor according to the present embodiment can be intentionally reduced. Thus, it is possible to reduce the stiff difference between the upper and lower walls and the side walls in the tail pipe section end section (outlet). The compulsion deformation can be reduced which is caused due to thermal stress generated in the tail pipe section end portion (outlet) on the operation of the gas turbine combustor. Also, it becomes possible to reduce the high stress easy to generate in the side plate. In the present embodiment, the gas turbine combustor having a high fatigue resistance can be realized. Thus, the gas turbine combustor with high reliability can be provided.
The basic components and structure of the gas turbine combustor of the second embodiment are the same as those of the gas turbine combustor of the first embodiment. However, in the second embodiment, the shapes of an engaging portion of an upper flange 110a and an upper seal 30a and an engaging portion of a lower flange 110b and a lower seal 30b are different from those of the first embodiment. The shapes different from the first embodiment and the effect of the shapes will be described.
In the second embodiment, as shown in
In the gas turbine combustor according to the present embodiment, the height of the flange provided in each of the upper and lower walls of the end portion (outlet) of the tail pipe section can be suppressed to the minimum height necessary for the flange and the seal section to engage. The stiffness of the flange in each of the upper and lower walls of the end portion (outlet) of the tail pipe section can be intentionally reduced. Thus, a stiff difference can be suppressed between the upper and lower walls of the end portion (outlet) of the tail pipe section and the side walls. As a result, the compulsion deformation caused due to the thermal stress generated in the end portion (outlet) of the tail pipe section on the operation of the gas turbine combustor, and it becomes possible to reduce the high stress easy to generate in the side plate. In the present embodiment, the gas turbine combustor with the high fatigue resistance can be realized and the reliability of the gas turbine combustor improves.
As shown in
In the present embodiment, the upper flange 130a is not provided with a comb-shaped gap in the horizontal direction. A convex section 135a is engaged with a concave section of the upper seal 50a to connect the upper flange 130a and the upper seal 50a. In the same manner, in the connection of the lower flange 130b and the lower seal 50b, the convex section 135b is engaged with the concave section of the lower seal 50b in the horizontal direction so that the lower flange 130b and the lower seal 50b are connected. After the engagement, positioning pins 5a and 5b are inserted in the vertical direction, respectively. Thus, the flanges 130a and 130b, and the seal sections 50a and 50b are fixed, respectively. In the present embodiment, the heights (thickness) of the upper flange 130a and the upper seal 50a, and the heights of the lower flange 130b and the lower seal 50b (in a direction perpendicular to the flow direction of the burning gas) can be more reduced based on the shape of the engaging portion of the upper flange 130a and the upper seal 50a, and the shape of the engaging portion of the lower flange 130b and the lower seal 50b, compared with the second embodiment.
In the gas turbine combustor according to the present embodiment, the stiffness of the flange in each of the upper and lower walls of the end portion (outlet) of the tail pipe section can be intentionally reduced through the reduction of the height of the flange provided in each of the upper and lower walls of the end portion (outlet) of the tail pipe section. Thus, the stiffness difference can be reduced between the upper and lower walls of the end portion (outlet) of the tail pipe section and the side walls. Also, compulsion deformation can be suppressed which is caused due to the thermal stress generated in the end portion (outlet) of the tail pipe section on the operation of the gas turbine combustor. Also, it becomes possible to reduce the high stress easy to generate in the side plate. In the present embodiment, the gas turbine combustor with the high fatigue resistance can be realized and the reliability of the gas turbine combustor improves.
The basic structure of the gas turbine combustor according to the present embodiment is the same as that of the gas turbine combustor according to the first embodiment. However, in the present embodiment, the gas turbine combustor according to the present embodiment is not provided with the upper flange and the lower flange. An upper seal supporting section 120a is provided in a gusset 4 to support the upper seal 40a to be inserted to the end portion (outlet) of the tail pipe section. A lower seal supporting section 120b is provided on the surface opposite to the position it which the gusset 4 is provided to insert the lower seal 40b.
In the present embodiment, as shown in
In the present embodiment, since the seal sections are connected with the main body 3 of the tail pipe section without any flanges on the upper and lower walls of the end portion (outlet) of the tail pipe section, the stiffness difference between the upper and lower walls of the end portion (outlet) of the tail pipe section and the side walls can be greatly reduced. Thus, the compulsion deformation can be suppressed which is caused due to the thermal stress generated in the end portion (outlet) of the tail pipe section on the operation of the gas turbine combustor. Also, it becomes possible to reduce the high stress easy to generate in the side plate. In the present embodiment, the gas turbine combustor with the high fatigue resistance can be realized and the reliability of the gas turbine combustor improves.
The basic components and structure of the gas turbine combustor in the fifth embodiment are the same as those of the gas turbine combustor of the first embodiment. However, in the present embodiment, slits 6 are provided on optional positions of an upper flange 140a and a lower flange 140b to reduce the stiffness of the flange appropriately. The shapes of components different from those of the first embodiment and the effect of the shapes will be described below.
In the present embodiment, as shown in
In the gas turbine combustor according to the present embodiment, the stiffness of the flange in each of the upper and lower walls of the end portion (outlet) of the tail pipe section can be intentionally reduced by the slit 6 provided for the flange in each of the upper and lower walls of the end portion (outlet) of the tail pipe section. Thus, the stiff difference can be reduced between the upper and lower walls of the end portion (outlet) of the tail pipe section and the side walls. Also, the compulsion deformation can be reduced which is caused due to the thermal stress generated in the end portion (outlet) of the tail pipe section on the operation of the gas turbine combustor. Also, it becomes possible to reduce the high stress easy to generate in the side plate. In the present embodiment, the gas turbine combustor with the high fatigue resistance can be realized and the reliability of the gas turbine combustor improves.
The basic components and structure of the gas turbine combustor according to the present embodiment are the same as those of the gas turbine combustor of the first embodiment. However, in the present embodiment, openings 7 of appropriate sizes are provided in optional positions of the upper flange 150a and the lower flange 150b. When the upper flange 150a and the seal section are engaged and the lower flange 150b and the seal section are engaged, a shield plate 9 is provided on a back position of the opening 7 for the purpose to prevent cooling air flowing through the tail pipe main body 3 from leaking through the opening 7. The shield plate 9 is welded along the periphery of the opening 7 in the upper flange 150a or the lower flange 150b.
In the present embodiment, as shown in
In the present embodiment, since the shield plate 9 is provided on the back of the opening 7, it is possible to prevent cooling air flowing through the main body 3 of the tail pipe section from leaking from the opening 7, and the improvement of the reliability is attained at a same time.
In the gas turbine combustor according to the present embodiment, the stiffness of the flange in each of the upper and lower walls of the end portion (outlet) of the tail pipe section can be intentionally reduced with the opening 7 provided for each of the upper and lower walls of the end portion (outlet) of the tail pipe section. Thus, the stiff difference can be reduced between the upper and lower walls of the end portion (outlet) of the tail pipe section and the side wall. Also, the compulsion deformation can be reduced which is caused due to the thermal stress generated in the end portion (outlet) of the tail pipe section on the operation of the gas turbine combustor. The high stress easy to generate in the side plate can be reduced. In the present embodiment, the gas turbine combustor with the high fatigue resistance can be realized and the reliability of the gas turbine combustor can be improved.
The basic components and structure of the gas turbine combustor of the seventh embodiment are the same as those of the gas turbine combustor of the first embodiment. However, in the present embodiment, when the flanges 160a and 160b and the seal sections 80a and 80b are engaged, respectively, a shield plate 9 for seal is provided along each of the upper flange 160a and the lower flange 160b, for the purpose to prevent the burning gas from leaking from a flow path. Also, the upper flange 160a and the lower flange 160b and the shield plate 9 are fixed by positioning pins 55, respectively.
In the present embodiment, as shown in FIG. 9B, the upper seal 80a is pushed to the upper flange 160a in the vertical direction and engaged with it, and the lower seal 80b is pushed to the lower flange 160b in the vertical direction and engaged with it. After the engagement, the positioning pins 5a and 5b are inserted in suitable positions, to fix the flanges 160a and 160b, and the seal sections 80a and 80b.
In the present embodiment, like the first embodiment, the heights (the length in the perpendicular direction to the flow direction of the burning gas) of the upper flange 160a and the lower flange 160b are set low. Thus, the stiffness of the upper and lower walls of the end portion (outlet) of the tail pipe section can be reduced. Also, a warp of the side wall can be reduced which is caused due to the thermal stress generated due to the stiffness difference between the upper and lower walls of the end portion (outlet) of the tail pipe section and the side wall on the operation of the gas turbine combustor of the present embodiment.
Moreover, in the present embodiment, the shield plate 9 is arranged along each of the flanges 160a and 160b. Therefore, it is possible to prevent the burning gas from leaking from gaps between the flanges 160a and 160b, and the seal sections 80a and 80b, and the improvement of the reliability is attained at a same time. In the present embodiment, the gas turbine combustor with the high fatigue resistance can be realized and the reliability of the gas turbine combustor improves.
The basic components and structure of the gas turbine combustor according to the present embodiment are the same as those of the gas turbine combustor of the first embodiment. However, the rear ends of the upper flange 170a and lower flange 170b of the present embodiment are provided with the slits 6 extending in the horizontal direction, respectively. In the present embodiment, the upper flange 170a and the lower flange 170b are engaged with the upper seal 90a and the lower seal 90b, respectively. Then, by inserting positioning pins 5a and 5b into suitable positions in the horizontal direction, the flanges 170a and 170b, and the seal sections 90a and 90b are fixed, respectively.
In the present embodiment, the slits extending in the horizontal direction (the flow direction of burning gas) are provided in the rear ends of the upper flange 170a and lower flange 170b. Thus, thermal expansion deformation caused in the upper and lower walls of the end portion (outlet) of the tail pipe section on the operation of the gas turbine combustor operation is absorbed by the slit 6 and is cancelled by this. Thereby, the stiffness of the flange in each of the upper and lower walls of the end portion (outlet) of the tail pipe section is reduced. Also, a warp of the side wall can be reduced which is caused due to the thermal stress generated due to the stiff difference between the upper and lower walls of the end portion (outlet) of the tail pipe section and the side wall on the operation of the gas turbine combustor of the present embodiment. In the present embodiment, the gas turbine combustor with the high fatigue resistance can be realized and the reliability of the gas turbine combustor improves.
According to the present invention, by reducing the stiffness of the flange provided for the upper and lower walls of the end portion (outlet) of the tail pipe section in the gas turbine combustor intentionally, it is possible to reduces the compulsion deformation of the side plates of the tail pipe section, and it is possible to reduce high stress generated in the side plate. Thus, the gas turbine combustor can be provided in which the fatigue resistance of the combustor is improved.
Number | Date | Country | Kind |
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2005-106811 | Apr 2005 | JP | national |
Filing Document | Filing Date | Country | Kind | 371c Date |
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PCT/JP06/05449 | 3/17/2006 | WO | 4/2/2007 |