Gas turbine combustion device

• US 6,688,107 B2
• Filed: 12/21/2001
• Issued: 02/10/2004
• Est. Priority Date: 12/26/2000
• Status: Expired due to Term

• Current Assignee: Mitsubishi Heavy Industries, Ltd.
• Original Assignee: Mitsubishi Heavy Industries, Ltd.
• Inventors: Ono, Masaki, Tanaka, Katsunori, Ikeda, Kazufumi, Nishimura, Masaharu, Ohnishi, Keizo
• Primary Examiner(s): Gartenberg, Ehud
• Application Number:
  US10/023,897
• Publication Number:
  US 20020078676A1
• Time in Patent Office: 781 Days
• Field of Search: 60/393.7, 607/25, 431/114
• US Class Current: 60/725
• CPC Class Codes: F23M 20/005 Noise absorbing means
• CPC Class Codes: F23R 3/002 Wall structures F23R3/02 and F23R3/007 take precedence

Abstract

A gas turbine combustion device comprises a plurality of combustion devices. Each combustion device has an inner cylinder and a tail cylinder in a vehicle chamber. An acoustic sleeve is provided between each inner cylinder and a corresponding outer cylinder in the vehicle chamber. An acoustic coupling effect with a vehicle chamber can be reduced.

Claims

1. A gas turbine combustion device comprising a plurality of combustion devices provided in a combustor housing, each of said combustion devices having an inner cylinder and a tail cylinder, further comprising a porous structure on a radially outward side wall relative to said cylinder, that is located near an opening end directing the air flow upstream between said wall and said cylinder of said combustion device.

2. A gas turbine combustion device as claimed in claim 1 further comprising at least one of a sintered metal mesh, a ceramic piece and a porous board at an outer side of said porous structure.

3. A gas turbine combustion device as claimed in claim 1, further comprising a contraction in a flow path near said opening portion.

4. A gas turbine combustion device as claimed in claim 1 further comprising a porous board located at a position perpendicular to a combustion flow at an upstream side of said combustion device.

5. A gas turbine combustion device as claimed in claim 1, further comprising a board having a narrow slit near an upstream opening portion of said combustion device.

6. The gas turbine combustion device of claim 3, wherein the porous structure is arranged so as to reduce an acoustic coupling between said combustor housing and said combustion device.