Gas turbine combustor

Patent metadata

Field	Value
Publication number	US-2016377290-A1
Application number	US-201615188208-A
Country	US
Kind code	A1
Filing date	Jun 21, 2016
Priority date	Jun 26, 2015
Publication date	Dec 29, 2016
Grant date	—

Abstract

A gas turbine combustor has a burner with an inner casing and an outer casing, and an airflow path that supplies air between them. An opening introduces air from an outer circumferential side to an inner circumferential side of the inner casing of the combustor and an obstacle impedes the flow of the air upstream of the opening portion. The obstacle is formed by a perforated plate having an opening ratio representing a ratio of cross-sectional area of an opening portion of the holes formed in the obstacle to the sum of the cross-sectional area of the opening portion of the holes, and the cross-sectional area of the shielding portion that shields the flow of the air is low on an inner circumferential side of the obstacle and high on an outer circumferential side of the obstacle.

First claim

1 . A gas turbine combustor comprising:
a combustor head portion having a burner and injects air and a fuel from the burner; a combustion chamber portion having a combustion chamber located downstream of the combustor head portion, the combustion chamber portion mixing the fuel and the air injected from the burner and burning the fuel to generate a combustion gas in the combustion chamber; a combustor tail portion having a partition located downstream of the combustion chamber portion and forms a flow path that allows the combustion gas to flow down, the combustor tail portion allowing the combustion gas generated in the combustion chamber to flow down the flow path formed by the partition; an inner casing provided in the combustor head portion to surround the burner, and an outer casing provided to surround an outer circumference of the inner casing; and an airflow path formed between the inner casing and the outer casing and supplies air, wherein the inner casing is provided with an opening portion that introduces the air supplied through the airflow path, from an outer circumferential side of the inner casing to an inner circumferential side of the inner casing, an obstacle that impedes flow of the air is provided in the airflow path on an upstream side of the opening portion, and the obstacle is formed by a perforated plate comprising a plurality of holes that flow a stream of the air, and the obstacle is configured such that an opening ratio representing a ratio of cross-sectional area of an opening portion of the hole formed in the obstacle to the sum of the cross-sectional area of the opening portion of the hole and cross-sectional area of a shielding portion that shields the flow of the air is low on an inner circumferential side of the obstacle and high on an outer circumferential side of the obstacle.

2 . The gas turbine combustor according to claim 1 , wherein, a combustor head portion having the burner and injects air and a fuel from the burner; a combustion chamber portion having a combustion chamber located downstream of the combustor head portion, the combustion chamber portion mixing the fuel and the air injected from the burner and burning the fuel to generate a combustion gas in the combustion chamber; and a combustor tail portion having a partition located downstream of the combustion chamber portion and forms a flow path that allows the combustion gas to flow down, the combustor tail portion allowing the combustion gas generated in the combustion chamber to flow down the flow path formed by the partition.

3 . A gas turbine combustor according to claim 1 , wherein, the combustor head portion that injects air and a fuel from a pilot burner provided at a central portion on a axial center side, and a plurality of main burners provided on an outer circumferential side of the pilot burner.

4 . The gas turbine combustor according to claim 1 , wherein the holes are formed in the obstacle such that a length of a peripheral portion defining the hole relative to an opening portion cross-sectional area of the hole is large on the inner circumferential side of the obstacle and small on the outer circumferential side of the obstacle.

5 . The gas turbine combustor according to claim 3 , wherein the obstacle provided in the airflow path is located only on an inner circumferential side in the airflow path so as not to impede the flow of the air on an outer circumferential side in the airflow path, and a guide plate that extends parallel to a longitudinal direction of the airflow path is provided on an outer circumferential end face of the obstacle.

6 . The gas turbine combustor according to claim 1 , wherein the obstacle is located with an inner circumferential end face connected to the outer circumference of the inner casing of the combustor, and an outer circumferential end face forming a gap with an inner circumference of the outer casing.

Assignees

• Mitsubishi Hitachi Power Sys

Inventors

• Okazaki Hirofumi
• Orii Akihito
• Uruno Tomoki

Classifications

• F23R3/286

  having fuel-air premixing devices (F23R3/30 takes precedence) · CPC title

• F23R3/54

  Reverse-flow combustion chambers · CPC title

• F23R3/50

  Combustion chambers comprising an annular flame tube within an annular casing (toroidal combustion chambers F23R3/52) · CPC title

• F23R3/02 Primary

  characterised by the air-flow or gas-flow configuration (reverse- flow combustion chambers F23R3/54; cyclone or vortex type combustion chambers F23R3/58) · CPC title

• F23R3/26

  Controlling the air flow · CPC title