Transition piece for non-annular gas turbine combustion chambers

• US 20030167776A1
• Filed: 03/19/2003
• Published: 09/11/2003
• Est. Priority Date: 06/16/2000
• Status: Abandoned Application

• Current Assignee: Nuovo Pignone SPA (Nuovo Pignone International SRL)
• Original Assignee: Nuovo Pignone SPA (Nuovo Pignone International SRL)
• Inventors: Coppola, Alessandro
• Application Number:
  US10/311,251
• Publication Number:
  US 20030167776A1
• Time in Patent Office: Days
• US Class Current: 60/800
• 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

Abstract

A transition piece (10) for non-annular gas turbine combustion chambers has a projecting connection arm (22) for support on the turbine stator, wherein the projecting connection arm (22) makes it possible to obtain a lead-in axis with an angle of between 5° and 7° relative to an axis, which is parallel to the axis of the machine, and is perpendicular to the plane on which there lies the frame for interfacing of the transition piece (10) with the ring of nozzles of the first stage of the gas turbine.

Claims

1. A transition piece (10) for non-annular gas turbine combustion chambers, suitable for connection between a non-annular gas turbine combustor (25) and a first stage (17) of the gas turbine (18), said transition piece (10) comprising a tubular body (11) with a cylindrical section (13), having an upstream end (14) for connection to the gas turbine combustor (25) and a downstream end (16), surrounding a flow aperture (15), for connection to the turbine (18) first stage (17), characterised in that a mount connector device (22) is provided on the transition piece (10), said mount connector device (22) comprising a tubular projection protruding upwardly from the body (11) of the transition piece (10) and then curving in a rearward direction for securing the transition piece (10) to said first stage (17) of the gas turbine (18), said transition piece (10) thus having a geometric profile so that the direction of the gas flow flowing at said upstream end (14) forms an angle of 5-7 degrees with an axis perpendicular to the plane on which said flow aperture (15) lies.

2. A transition piece (10) according to claim 1, characterised in that said cylindrical section (13) has an anti-wear deposit, made of Stellite 6 or another similar material, at said upstream end (14).

3. A transition piece (10) according to claim 1, characterised in that a deposit of the TBC type is provided on the inner surface of the transition piece (10).

4. A transition piece (10) according to claim 1, characterised in that said tubular body (11) is made of Nimonic 263 or Hastelloy-X.