Gas turbine combustor
View Patent ↗An object of the present invention is to provide a gas turbine combustor with improved fatigue resistance of a combustor. It is possible to intentionally reduce a stiffness of each of flanges of upper and lower walls of an end portion (outlet) of the tail pipe of the gas turbine combustor. It is possible to reduce a stiff difference between the upper and lower walls of the end portion (outlet) of the tail pipe section and side walls. Thus, it is possible to reduce compulsion deformation 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 to reduce high stress easy to generate in the side plate. As a result, the gas turbine combustor with high fatigue resistance can be realized.
1. A gas turbine combustor comprising:
a combustor main body;
a tail pipe connected with said combustor main body to spout out burning gas; and
a seal section provided to prevent said burning gas from leaking from a space of a plurality of said tail pipes annularly arranged around one axis, and wherein:
said tail pipe has upper and lower walls opposite to each other in a radius direction of said axis in an end portion of said tail pipe, and a first stiffness reducing engaging portion provided for said upper and lower walls for reducing the stiffness of said upper and lower walls,
said seal section has a second engaging portion for engagement with said first stiffness reducing engaging portion in a front end of said seal section,
said first stiffness reducing engaging portion comprises one set of flanges opposite to each other in the radius direction, and further comprising:
a shield plate provided along each of said flanges of the one set,
wherein said shield plate and said flange are fixed by a shield plate fixing member, and
said tail pipe and said seal section are connected, by engaging each of said flanges of the one set in which said shield plate is provided, with said second engaging portion.
2. A gas turbine combustor comprising:
a combustor main body;
a tail pipe connected with said combustor main body to spout out burning gas; and
a seal section provided to prevent said burning gas from leaking from a space of a plurality of said tail pipes annularly arranged around one axis, wherein:
said tail pipe has upper and lower walls opposite to each other in a radius direction of said axis in an end portion of said tail pipe, and a first stiffness reducing engaging portion provided for said upper and lower walls for reducing the stiffness of said upper and lower walls, and
said seal section has a second engaging portion for engagement with said first stiffness reducing engaging portion in a front end of said seal section,
said first stiffness reducing engaging portion comprises one set of flanges provided to oppose each other in said radius direction and to extend in a flow direction of said burning gas, and
each of said flanges and said second engaging portion are engaged with each other in the flow direction of said burning gas,
each of said flanges has a convex section, and
said second engaging portion has a concave section which is engaged with said convex section to connect said tail pipe and said seal section.
3. A gas turbine combustor comprising:
a combustor main body;
a tail pipe connected with said combustor main body to spout out burning gas; and
a seal section provided to prevent said burning gas from leaking from a space of a plurality of said tail pipes annularly arranged around one axis, wherein:
said tail pipe has upper and lower walls opposite to each other in a radius direction of said axis in an end portion of said tail pipe, and a first stiffness reducing engaging portion provided for said upper and lower walls for reducing the stiffness of said upper and lower walls, and
said seal section has a second engaging portion for engagement with said first stiffness reducing engaging portion in a front end of said seal section,
said tail pipe further comprising:
a gusset provided on a position apart from the end portion of said tail pipe to extend in a perpendicular direction to a pipe surface of said tail pipe and to fix said tail pipe to a housing of the gas turbine,
said gusset has a first supporting section to engage said second engaging portion,
said tail pipe has a second supporting section provided on the pipe surface of said tail pipe opposite to said gusset to engage said second engaging portion, and
said tail pipe and said seal section are connected by engaging said first and second supporting sections as first engaging portion and said second engaging portion.
4. A gas turbine combustor comprising:
a combustor main body;
a tail pipe connected with said combustor main body to spout out burning gas; and
a seal section provided to prevent said burning as from leaking from a space of a plurality of said tail annularly arranged around one axis, wherein:
said tail pipe has upper and lower walls opposite to each other in a radius direction of said axis in an end portion of said tail pipe, and a first stiffness reducing engaging portion provided for said upper and lower walls for reducing the stiffness of said upper and lower walls, and
said seal section has a second engaging portion for engagement with said first stiffness reducing engaging portion in a front end of said seal section,
said first stiffness reducing engaging portion comprising:
one set of said flanges opposite each other in the radius direction, and wherein
each of said flanges has an opening.
5. The gas turbine combustor according to claim 4 , wherein:
a seal plate is provided along an external circumference of said opening,
said external circumference and said seal plate are welded, and
said tail pipe and said seal section are connected by engaging said one set of said flanges and said seal plate connected to said set and said second engaging portion.
6. A gas turbine combustor comprising:
a combustor main body;
a tail pipe connected with said combustor main body to spout out burning gas; and
a seal section provided to prevent said burning gas from leaking from a space of a plurality of said tail pipes annularly arranged around one axis, and wherein:
said tail pipe has upper and lower walls opposite to each other in a radius direction of said axis in an end portion of said tail pipe, and a first stiffness reducing engaging portion provided for said upper and lower walls for reducing the stiffness of said upper and lower walls,
said seal section has a second engaging portion for engagement with said first stiffness reducing engaging portion in a front end of said seal section,
said first stiffness reducing engaging portion comprising one set of flanges opposite to each other in the circumferential direction, and
each of said flanges has a slit extending in a direction perpendicular to the flow direction of said burning gas.
7. A gas turbine combustor comprising:
a combustor main body;
a tail pipe connected with said combustor main body to spout out burning gas; and
a seal section provided to prevent said burning gas from leaking from a space of a plurality of said tail pipes annularly arranged around one axis, and wherein:
said tail pipe has upper and lower walls opposite to each other in a radius direction of said axis in an end portion of said tail pipe, and a first stiffness reducing engaging portion provided for said upper and lower walls for reducing the stiffness of said upper and lower walls,
said seal section has a second engaging portion for engagement with said first stiffness reducing engaging portion in a front end of said seal section,
said first stiffness reducing engaging portion comprising one set of flanges opposite to each other in the circumferential direction, and
each of said flanges has a slit extending in the flow direction of said burning gas.