Combustor liner

• US 8,863,527 B2
• Filed: 04/30/2009
• Issued: 10/21/2014
• Est. Priority Date: 04/30/2009
• Status: Active Grant

• Current Assignee: Rolls-Royce Corporation (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce Corporation (Rolls-Royce Holdings Plc)
• Inventors: Holcomb, Marcus Timothy, Taylor, Todd, Yount, Randall E.
• Primary Examiner(s): Wongwian, Phutthiwat
• Assistant Examiner(s): SUTHERLAND, STEVEN M
• Application Number:
  US12/433,104
• Publication Number:
  US 20100275606A1
• Time in Patent Office: 2,000 Days
• Field of Search: 607/96, 607/98, 607/99, 608/00, 60752-760
• US Class Current: 60/752
• CPC Class Codes: F23R 3/002 Wall structures F23R3/02 and F23R3/007 take precedence
• CPC Class Codes: F23R 3/283 Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
• CPC Class Codes: F23R 3/42 characterised by the arrangement or form of the flame tubes or combustion chambers
• CPC Class Codes: Y10T 29/4932 Turbomachine making

Abstract

A combustor liner for a turbine engine is disclosed herein. The combustor liner includes an inner liner surface operable to define at least part of a combustion chamber in a turbine engine. The inner liner surface extends along a portion of a chordal arc on a first side of the chordal arc. The combustor liner also includes a bearing surface operable to support a floating dome panel. At least part of the bearing surface is spaced from the chordal arc on a second side of the chordal arc opposite the first side.

Claims

1. A combustor liner for a turbine engine comprising:

an inner liner surface operable to define at least part of a combustion chamber in a turbine engine, wherein the inner liner surface has a shape defined by a chordal arc and extends along the chordal arc, and wherein a wall of the combustion liner is disposed on a first side of said chordal arc;

a bearing surface operable to support a floating dome panel, wherein at least part of said bearing surface is spaced from said chordal arc on a second side of said chordal arc opposite said first side;

a liner portion defining said inner liner surface and having an outer surface opposite said inner liner surface;

a hanger portion fixed relative to said liner portion and including a first arm extending to a first distal end defining said bearing surface;

wherein said hanger portion further comprises a second arm extending to a second distal end spaced from said first distal end; and

wherein said first and second arms initially extend away from said chordal arc in opposite directions.

2. The combustor liner of claim 1 wherein all of said bearing surface is spaced from said chordal arc on said second side.

3. The combustor liner of claim 1 wherein said bearing surface is transverse to said chordal arc.

4. The combustor liner of claim 1 wherein said inner liner surface is one of convex and concave in facing the combustion chamber.

5. The combustor liner of claim 1 wherein said first arm is fully positioned on said second side of said chordal arc.

6. The combustor liner of claim 1 wherein said liner and hanger portions are further defined as being separately formed and fixed together.

7. The combustor liner of claim 1 wherein said second arm is positioned radially outward of said outer surface relative to said chordal arc.

8. The combustor liner of claim 7 wherein said first arm is partially positioned on said second side and partially positioned on said first side of said chordal arc.

9. The combustor liner of claim 1 wherein said first and second arms extend respective first and second distances in opposite directions from said chordal arc and then extend in intersecting directions after said respective first and second distances.

10. The combustor liner of claim 1 wherein both of said first and second arms extend transverse to said chordal arc.

11. The combustor liner of claim 1 wherein at least one of said first and second arms defines an s-shaped cross-section.

12. The combustor liner of claim 1 wherein one of said first and second arms extends from the other of said first and second arms.

13. A turbine engine comprising:

a floating dome panel encircling a centerline axis of the turbine engine; and

at least one combustor liner including;

an inner liner surface operable to define at least part of a combustion chamber, wherein the inner liner surface has a shape defined by a chordal arc and extends along the chordal arc, and wherein a wall of the combustion liner is disposed on a first side of said chordal arc;

a bearing surface operable to support said floating dome panel, wherein at least part of said bearing surface is spaced from said chordal arc on a second side of said chordal arc opposite said first side, wherein said floating dome panel is slidable along said bearing surface in a direction having a radial directional component relative to the centerline axis; and

a hanger portion having a first arm extending to a first distal end defining said bearing surface and a second arm extending to a second distal end spaced from said first distal end, wherein the first and second arms initially extend away from said chordal arc in opposite directions.

14. The turbine engine of claim 13 wherein said at least one combustor liner further comprises:

an outer combustor liner having a first inner liner surface and a first bearing surface supporting a radially outer edge of said floating dome panel, wherein the first inner liner surface has a first shape defined by a first chordal arc and extends along the first chordal arc; and

an inner combustor liner having a second inner liner surface and a second bearing surface supporting a radially inner edge of said floating dome panel, wherein the second inner liner surface has a second shape defined by a second chordal arc and extends along the second chordal arc, wherein a combustor axis extends equidistantly between said first and second chordal arcs and wherein said first and second bearing surfaces are positioned closer to said combustor axis than said first and second chordal arcs at the respective positions of said first and second bearing surfaces along said combustor axis.

15. The turbine engine of claim 14 wherein each of said inner and outer combustor liners further comprises:

a first arm extending to a first distal end defining said bearing surface;

a second arm extending to a second distal end spaced from said first distal end and including an aperture for receiving a fastener.