Crossfire tube assembly with inner tube having different curvatures

Patent metadata

Field	Value
Publication number	US-11098901-B2
Application number	US-201816182805-A
Country	US
Kind code	B2
Filing date	Nov 7, 2018
Priority date	Nov 8, 2017
Publication date	Aug 24, 2021
Grant date	Aug 24, 2021

Abstract

In a gas turbine combustor, a sectional shape in a radial direction of either one of an inner peripheral surface of a second inner tube member and an outer peripheral surface of a first inner tube member, in a fitting portion of a crossfire tube assembly, has a plurality of small-curvature portions having a curvature smaller than a reference curvature, the reference curvature being a curvature of a portion at a maximum distance from the center of the sectional shape. This configuration ensures the crossfire tube assembly is cooled, and the Possibility of thermal deformation or fire damage is lowered, without lowering the temperature of a combustion exhaust gas passing through the crossfire tube assembly of the gas turbine combustor.

First claim

What is claimed is:

1. A gas turbine combustor comprising:
a plurality of combustors each including a partition wall defining a combustion chamber, and an outer peripheral partition wall surrounding the partition wall and defining a combustion air flow passage between the outer peripheral partition and the partition wall; and
a crossfire tube assembly connecting a first combustor of the plurality of combustors to a second combustor of the plurality of combustors, wherein the first combustor is adjacent to the second combustor,
the crossfire tube assembly including an inner tube that connects the partition wall of the first combustor and the partition wall of the second combustor, an outer tube that surrounds the inner tube and connects the outer peripheral partition wall of the first combustor and the outer peripheral partition wall of the second combustor,
the inner tube being divided in an axial direction into a first inner tube member and a second inner tube member,
an end portion of the second inner tube member having an enlarged portion that has an inner diameter greater than an outer diameter of the first inner tube member, and
the first inner tube member and the second inner tube member forming a fitting portion such that part of the first inner tube member is located within the enlarged portion of the second inner tube member with a gap therebetween,
wherein a sectional shape at the fitting portion in a radial direction of either one of an inner peripheral surface of the second inner tube member or an outer peripheral surface of the first inner tube member has a plurality of small-curvature portions having a curvature than a reference curvature, the reference curvature being a curvature of a portion at a maximum distance from a center of the sectional shape, and
wherein the reference curvature is a reciprocal of the maximum distance.

2. The gas turbine combustor according to claim 1 , wherein the sectional shape of the small-curvature portions has zero curvature and is a straight line.

3. The gas turbine combustor according to claim 1 , wherein the sectional shape of the small-curvature portions has zero curvature and is a straight line, and the sectional shape of the reference curvature is a circular arc.

4. The gas turbine combustor according to claim 2 , wherein either the outer peripheral surface of the first inner tube member or the inner peripheral surface of the second inner tube member is provided with a plurality of plain surface portions extending in the axial direction, and wherein the plurality of plain surface portions form the small-curvature portions.

5. The gas turbine combustor according to claim 1 , wherein a length of the small-curvature portion in the axial direction is longer than a length of the fitting portion in the axial direction.

6. The gas turbine combustor according to claim 1 , wherein a length of the enlarged portion in the axial direction is equal to or more than 1.5 times a length of the fitting portion in the axial direction.

7. The gas turbine combustor according to claim 1 , wherein the inner tube is provided with an air hole through which combustion air flowing within a space between the outer tube and the inner tube is introduced into a space inside the inner tube.

8. The gas turbine combustor according to claim 7 , comprising a guide ring having a guide wall extending along an inside surface of the inner tube, wherein the guide wall is provided radially inward of the air hole.

9. The gas turbine combustor according to claim 1 , wherein the inner tube is connected the outer peripheral partition wall of the first combustor and the outer peripheral partition wall of the second combustor.

10. A gas turbine comprising the gas turbine combustor according to claim 1 .

11. A crossfire tube assembly comprising:
an inner tube that connects a partition wall of a first combustor to a partition wall of a second combustor, wherein the first combustor is adjacent to the second combustor, and an outer tube surrounds the inner tube and connects an outer peripheral partition wall of the first combustor and an outer peripheral partition wall of the second combustor,
inner tube being divided in an axial direction into a first inner tube member and a second inner tube member,
an end portion of the second inner tube member having an enlarged portion that has an inner diameter greater than an outer diameter of the first inner tube member, and
the first inner tube member and the second inner tube member forming a fitting portion such that part of the first inner tube member is located within the enlarged portion of the second inner tube member with a gap therebetween,
wherein a sectional shape at the fitting portion in a radial direction of either one of an inner peripheral surface of the second inner tube member or an outer peripheral surface of the first inner tube member has a plurality of small-curvature portions having a curvature than a reference curvature, the reference curvature being a curvature of a portion at a maximum distance from a center of the sectional shape, and
wherein the reference curvature is a reciprocal of the maximum distance.

Assignees

• Mitsubishi Power Ltd

Inventors

• Okazaki Hirofumi
• Koganezawa Tomomi
• Takahashi Hirokazu

Classifications

• F23R3/48 Primary

  Flame tube interconnectors, e.g. cross-over tubes · CPC title

• F23R3/002

  Wall structures (F23R3/02 and F23R3/007 take precedence) · CPC title

• F05D2240/35

  Combustors or associated equipment · CPC title

• F23C6/02

  in parallel arrangement · CPC title