Pyrospin combuster

• US 6,955,053 B1
• Filed: 07/01/2002
• Issued: 10/18/2005
• Est. Priority Date: 07/01/2002
• Status: Expired due to Term

• Current Assignee: Hamilton Sundstrand Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: Hamilton Sundstrand Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Piconi, Paul, Hayden, Chris, Vitale, Jack, Trees, Dietmar, Reichmann, Tony, Chen, Daih-Yeou
• Primary Examiner(s): Gartenberg, Ehud
• Application Number:
  US10/186,640
• Time in Patent Office: 1,205 Days
• Field of Search: 608/04, 607/52
• US Class Current: 60/804
• CPC Class Codes: F23R 2900/03041 Effusion cooled combustion chamber walls or domes
• CPC Class Codes: F23R 3/06 Arrangement of apertures along the flame tube
• CPC Class Codes: F23R 3/50 Combustion chambers comprising an annular flame tube within an annular casing toroidal combustion chambers F23R3/52
• CPC Class Codes: F23R 3/54 Reverse-flow combustion chambers
• CPC Class Codes: F23R 3/58 Cyclone or vortex type combustion chambers

Abstract

An annular combustor that has angled effusion holes through at least one surface of the combustor liner with the angle of the effusion holes oriented to cause the flow of air through the holes to facilitate swirling of the fuel and air within the combustor. The effusion holes thereby facilitate efficient cooling of the combustor liner combined with superior fuel/air mixing within the combustor.

Claims

1. For a gas turbine engine that employs an annular combustor with radial fuel injection, a gas turbine annular combustor that has an annular outlet and a liner with liner surfaces comprising a dome, an outer wall, and an inner wall, comprising:

angled effusion cooling holes in at least one of the liner surfaces that have a swirl angle from the surface in a direction that is generally tangential to the axial flow of combustion gas in the combustor toward the outlet to effectuate swirling of combustion gases in the combustor;

wherein the outer wall and the inner wall have angled cooling holes and the angled cooling holes have both a swirl angle and a downstream angle from the surface in a direction generally parallel the axial flow of combustion gas in the combustor toward the outlet;

and wherein the combustor has a dome with effusion cooling holes and associated cooling strips.

2. The gas turbine combustor set forth in claim 1, wherein the dome has the angled cooling holes.

3. The gas turbine combustor set forth in claim 1, wherein at least one of the outer and inner walls have air blast tubes.

4. The gas turbine combustor set forth in claim 1, wherein the swirl angle is in the range of approximately 45 to 90 degrees.

5. The gas turbine combustor set forth in claim 1, wherein the swirl angle changes gradually over at least one of the liner surfaces.

6. The gas turbine set forth in claim 1, wherein the downstream angle is in the range of approximately 15 to 45 degrees.