Gas turbine combustor

• US 7,032,386 B2
• Filed: 06/25/2002
• Issued: 04/25/2006
• Est. Priority Date: 06/27/2001
• Status: Expired due to Term

• Current Assignee: mitsubishi hitachi power systems, ltd. (Mitsubishi Heavy Industries, Ltd.)
• Original Assignee: Mitsubishi Heavy Industries, Ltd.
• Inventors: Tanaka, Katsunori, Mandai, Shigemi, Akizuki, Wataru, Saitoh, Keijirou, Kataoka, Masahito
• Primary Examiner(s): KIM, TAE JUN
• Application Number:
  US10/416,515
• Publication Number:
  US 20040074236A1
• Time in Patent Office: 1,400 Days
• Field of Search: 607/48, 607/57
• US Class Current: 60/757
• CPC Class Codes: F23R 2900/03042 Film cooled combustion chamber walls or domes
• CPC Class Codes: F23R 3/04 Air inlet arrangements

Abstract

A combustor for a gas turbine has an arrangement to form a layer of cooling-air on an inner surface of a liner of a combustion chamber. This layer of the cooling air extends from a fuel nozzle block of the combustor toward a downstream side with respect to the liner.

Claims

1. A combustor for a gas turbine, comprising:

a liner;

a combustion chamber formed within the liner, the chamber having an opening at an upstream side thereof

a fuel nozzle block disposed within the opening of the chamber;

a ring for forming a cooling-air layer toward a downstream side with respect to the liner, wherein the ring is disposed between the liner and the fuel nozzle block with predetermined gaps for guiding the cooling-air toward the combustion chamber and forming the cooling-air layer on an inner surface of the liner; and

a cooling-air supplying hole bored in the liner, wherein the hole is bored facing the ring;

wherein the ring is fixed to the inner surface of the liner at an upstream side of the cooling-air supplying hole.

2. The combustor according to claim 1, further comprising:

a plurality of spacers disposed circumferentially between the liner and the ring at predetermined intervals.