Gas turbine combustion chamber having a flow sleeve with a plurality of integrated segments
View Patent ↗A gas turbine combustion chamber is provided, including a flow sleeve structure with an improved anti-vibration performance. A gas turbine combustion chamber of the present invention includes a liner, a transition piece, and a flow sleeve including a plurality of segments and integrated by welding a tie piece along joint portions of the segments. The tie piece includes a first member and a second member, the first member continuously extending along a longitudinal direction of the joint portions of the segments and being arranged to cover the joint portions, and the second member being formed at an end portion of the first member, having a width wider than the first member, and including a recess.
1. A gas turbine combustion chamber comprising:
a liner forming a combustion zone;
a transition piece connected to a downstream side of the liner; and
a flow sleeve including a plurality of segments, the flow sleeve housing the transition piece, and the plurality of segments being integrated with each other by welding a tie piece along each of a plurality of joint portions of the plurality of segments,
wherein each of the tie pieces includes a first member and a second member, the first member continuously extending along a longitudinal direction of one of the plurality of joint portions of the plurality of segments and being arranged to cover the one of the plurality of joint portions, the second member being formed at an end portion of the first member, the second member having a width wider than a width of the first member, and the second member including a recess;
wherein a width of the recess at an end portion of the second member is wider than the width of the first member;
wherein the width of the first member is denoted by W1, the width of the second member is denoted by W2, the width of the recess at the end portion of the second member is denoted by W3, and a relationship between W1, W2, and W3 is W1<W3<W2;
wherein the second member includes first outer side surfaces, all of which are inclined at a same acute angle with respect to joint faces of the plurality of segments, and second outer side surfaces parallel to the joint faces;
wherein the first outer side surfaces and the second outer side surfaces are outermost side surfaces of the second member, with respect to the joint faces, in a width direction along width W2;
wherein each of the first outer side surfaces is connected to a respective outermost side surface of the first member, with respect to the joint faces in a width direction along width W1; and
wherein each of the first outer side surfaces is connected to a respective one of the second outer side surfaces.
2. The gas turbine combustion chamber according to claim 1 ,
wherein the recess is semicircular in shape.
3. The gas turbine combustion chamber according to claim 1 ,
wherein the recess is rectangular in shape.
4. The gas turbine combustion chamber according to claim 1 ,
wherein the recess is formed by a combination of at least surfaces perpendicular to the joint faces of the plurality of segments and surfaces inclined with respect to the joint faces of the plurality of segments.
5. The gas turbine combustion chamber according to claim 1 ,
wherein the first outer side surfaces and the second outer side surfaces are disposed adjacent to the recess.