Combustor with ring part having protrusions and gas turbine including the combustor

• US 9,939,158 B2
• Filed: 02/18/2014
• Issued: 04/10/2018
• Est. Priority Date: 03/15/2013
• Status: Active Grant

• Current Assignee: Mitsubishi Power Limited (Mitsubishi Heavy Industries, Ltd.)
• Original Assignee: mitsubishi hitachi power systems, ltd. (Mitsubishi Heavy Industries, Ltd.)
• Inventors: Taniguchi, Kenta, Motoyama, Norihiko, Nakamura, Yoshiro
• Primary Examiner(s): SUTHERLAND, STEVEN M
• Application Number:
  US14/770,638
• Publication Number:
  US 20160003481A1
• Time in Patent Office: 1,512 Days
• CPC Class Codes: F01D 9/023 Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
• CPC Class Codes: F02C 3/04 having a turbine driving a compressor power transmission arrangements F02C7/36; control of working fluid flow F02C9/16
• CPC Class Codes: F23R 2900/00012 Details of sealing devices
• CPC Class Codes: F23R 3/42 characterised by the arrangement or form of the flame tubes or combustion chambers
• CPC Class Codes: F23R 3/46 Combustion chambers comprising an annular arrangement of several essentially tubular flame tubes within a common annular casing or within individual casings
• CPC Class Codes: F23R 3/54 Reverse-flow combustion chambers

Abstract

A combustor includes a first tube which supplies fuel and air from an opening formed in a distal end thereof, and a second tube which is configured such that flames are formed on an inner circumferential side thereof by the fuel and the air and the distal end of the first tube is inserted into an inner circumferential side of a proximal end thereof. The first tube includes a first tube main body and a ring part forming the distal end of the first tube. The ring part has a main body of a tubular shape and a plurality of protrusions that are integrally formed with the main body on an outer circumferential surface of the main body and protrude radially outward. When viewed in an axial direction, the outer circumferential surface of the main body has a polygonal cross-sectional shape within a range within which the protrusions are formed.

Claims

1. A combustor comprising:

a first tube which supplies fuel and air from an opening formed in a distal end thereof; and

a second tube which is configured such that the distal end of the first tube is inserted into an inner circumferential side of a proximal end thereof,

wherein;

the first tube includes a first tube main body and a ring part forming the distal end of the first tube,

the ring part has a main body of a tubular shape and protrusions that are integrally formed with the main body on an outer circumferential surface of the main body and protrude radially outward,

when viewed in an axial direction along an axis of the first tube, the outer circumferential surface of the main body has a polygonal cross-sectional shape within a range within which the protrusions are formed, and

the main body includes a polygonal ring part on which the protrusions are formed, and a restrictor part at a distal end side relative to the polygonal ring part and an outer circumferential surface of which is formed in a cylindrical shape at a radially outer circumferential side relative to an outer circumferential surface of the polygonal ring part.

2. The combustor according to claim 1, wherein the protrusions are formed in centers of outer circumferential planes of the polygonal ring part in a circumferential direction.

3. The combustor according to claim 2, wherein, when viewed in a radial direction along a radius of the first tube, each of the protrusions has a spindle cross-sectional shape along the axial direction.

4. A gas turbine comprising:

the combustor according to claim 2; and

a turbine driven by a combustion gas delivered from the second tube of the combustor.

5. The combustor according to claim 1, wherein, when viewed in a radial direction along a radius of the first tube, each of the protrusions has a spindle cross-sectional shape along the axial direction.

6. A gas turbine comprising:

the combustor according to claim 1; and

a turbine driven by a combustion gas delivered from the second tube of the combustor.