Cross fire tube with guide ring and angled cooling holes

Patent metadata

Field	Value
Publication number	US-10520196-B2
Application number	US-201715671793-A
Country	US
Kind code	B2
Filing date	Aug 8, 2017
Priority date	Aug 9, 2016
Publication date	Dec 31, 2019
Grant date	Dec 31, 2019

Abstract

The present invention provides a multi-can type gas turbine combustor including a plurality of combustors that mix and burn fuel and the air, the combustors being connected by a crossfire tube assembly. The gas turbine cools the crossfire tube assembly without lowering the temperature of a combustion exhaust gas passing through the crossfire tube assembly and prevents thermal deformation and fire damage of the crossfire tube assembly. In a gas turbine according to the present invention, a guide ring that guides a current of the air is provided in a position opposed to air holes. One side end portion of an annular space configured between the guide ring and a crossfire tube assembly is opened to a space on the inside of the crossfire tube assembly. The other end portion is a closed end connected to a partition wall configuring the crossfire tube assembly. The length of an annular space between the air holes and the closed end is set to three times or more as large as the diameter of the air holes. Further, a part of the air holes is drilled to tilt to the closed end of the annular space to cool the crossfire tube assembly including the guide ring with a small cooling air amount.

First claim

The invention claimed is:

1. A gas turbine combustor comprising a plurality of combustors, a first combustor of the plurality of combustors being connected by a crossfire tube assembly to a second combustor of the plurality of combustors, the first combustor having an ignitor for combustion initiation in the first combustor and for ignition in second combustor via the cross fire tube assembly, wherein
the crossfire tube assembly includes:
an outer tube, and
an inner tube within the outer tube, through which a combustion exhaust gas of the first combustor flows to the second combustor;
the inner tube includes:
a plurality of air holes that introduce a cooling air flow into the inner tube from an outside of the crossfire tube assembly, wherein each of the plurality of air holes have an inlet on an outer diameter of the inner tube and an outlet on an inner diameter of the inner tube; and
a guide ring within the inner tube and concentric with the inner tube positioned opposite the plurality of air holes, the guide ring positioned for guiding the cooling air flow introduced by the plurality of air holes along the inner tube,
a first end of the guide ring has a flange, the flange connected to the inner diameter of the inner tube such that the flange prevents the cooling air flow from passing through the first end and,
a second end of the guide ring, wherein the second end of the guide ring is open to the inner tube such that the cooling airflow can pass into the inner tube, wherein
the first end of the guide ring is closer than the second end of the guide ring to the first combustor, wherein
a first group of the plurality of the air holes are angled towards the flange such that a portion of the cooling air flow is directed from each outlet of the first group of air holes towards the flange, and
a second group of the plurality of the air holes are angled at an angle that is different from the first group of air holes with respect to a central axis of the inner tube.

2. The gas turbine combustor according to claim 1 , wherein a distance from each center of the first group of air holes at their respective inlet on the outer diameter of the inner tube to the flange is three times or more as large as a diameter of the first group of air holes.

3. The gas turbine combustor according to claim 1 , wherein the inner tube comprises a first cylindrical member and a second cylindrical member, wherein the first cylindrical member is configured to fit into the second cylindrical member.

4. The gas turbine combustor according to claim 1 , wherein a protrusion section is provided between the inner tube and the outer tube.

5. A gas turbine combustor comprising a plurality of combustors, a first combustor of the plurality of combustors being connected by a crossfire tube assembly to a second combustor of the plurality of combustors, the first combustor having an ignitor for combustion initiation in the first combustor and for ignition in second combustor via the cross fire tube assembly, wherein
the crossfire tube assembly includes:
an outer tube, and
an inner tube within the outer tube, through which a combustion exhaust gas of the first combustor flows to the second combustor;
the inner tube includes:
a plurality of air holes that introduce a cooling air flow into the inner tube from an outside of the crossfire tube assembly, wherein each of the plurality of air holes have an inlet on an outer diameter of the inner tube and an outlet on an inner diameter of the inner tube; and
a guide ring within the inner tube and concentric with the inner tube positioned opposite the plurality of air holes, the guide ring positioned for guiding the cooling air flow introduced by the plurality of air holes along the inner tube,
a first end of the guide ring has a flange, the flange connected to the inner diameter of the inner tube such that the flange prevents the cooling air flow from passing through the first end and,
a second end of the guide ring, wherein the second end of the guide ring is open to the inner tube such that the cooling airflow can pass into the inner tube, wherein
the first end of the guide ring is closer than the second end of the guide ring to the first combustor, wherein
a first group of the plurality of the air holes are angled towards the flange such that a portion of the cooling air flow is directed from each outlet of the first group of air holes towards the flange, and
a second group of the plurality of the air holes are angled at an angle that is different from the first group of air holes with respect to a central axis of the inner tube, and
a first protrusion section within the guide ring between the plurality of cooling holes and the second end of the guide ring configured to suppress the cooling air flow out the second end of the guide ring.

6. The gas turbine combustor according to claim 5 , wherein a distance from each center of the first group of air holes at their respective inlet on the outer diameter of the inner tube to the flange is three times or more as large as a diameter of the first group of air holes.

7. The gas turbine combustor according to claim 5 , wherein the inner tube comprises a first cylindrical member and a second cylindrical member, wherein the first cylindrical member is configured to fit into the second cylindrical member.

8. The gas turbine combustor according to claim 5 , wherein the plurality of air holes are configured as drilled holes.

9. The gas turbine combustor according to claim 5 , wherein a second protrusion section is provided between the inner tube and the outer tube.

Assignees

• Mitsubishi Hitachi Power Sys

Inventors

• Okazaki Hirofumi
• Takahashi Hirokazu

Classifications

• F23R2900/03044

  Impingement cooled combustion chamber walls or subassemblies · CPC title

• F23R3/48 Primary

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

• F23R3/26 Primary

  Controlling the air flow · CPC title

• F23R3/06

  Arrangement of apertures along the flame tube · CPC title

• F23R3/08

  between annular flame tube sections, e.g. flame tubes with telescopic sections · CPC title