Segmented annular combustor

• US 4,158,949 A
• Filed: 11/25/1977
• Issued: 06/26/1979
• Est. Priority Date: 11/25/1977
• Status: Expired due to Term

• Current Assignee: Allison Engine Company, Inc.
• Original Assignee: General Motors Corporation (Motors Liquidation Co. GUC Trust)
• Inventors: Reider, Samuel B.
• Primary Examiner(s): Garrett, Robert E.
• Application Number:
  US05/854,758
• Time in Patent Office: 578 Days
• Field of Search: 60/39.32, 60/39.65, 60/39.69 R, 431/351, 431/352
• US Class Current: 60/800
• CPC Class Codes: F23R 3/002 Wall structures F23R3/02 and F23R3/007 take precedence
• CPC Class Codes: F23R 3/50 Combustion chambers comprising an annular flame tube within an annular casing toroidal combustion chambers F23R3/52

Abstract

An industrial gas turbine engine includes an inclined annular combustor made up of a plurality of support segments each including inner and outer walls of trapezoidally configured planar configuration extents and including side flanges thereon interconnected by means of air cooled connector bolt assemblies to form a continuous annular combustion chamber therebetween and wherein an air fuel mixing chamber is formed at one end of the support segments including means for directing and mixing fuel within a plenum and a perforated header plate for directing streams of air and fuel mixture into the combustion chamber; each of the outer and inner walls of each of the support segments having a ribbed lattice with tracks slidably supporting porous laminated replaceable panels and including pores therein for distributing combustion air into the combustion chamber while cooling the inner surface of each of the panels by transpiration cooling thereof.

Claims

1. A gas turbine engine combustor assembly comprising a plurality of support segments each including an outer wall and an inner wall, means joining said support segments to one another to form a continuously peripheral outer liner and inner liner defining an annular combustion zone therebetween, means for mixing and directing air and fuel into said combustion zone, each of said outer and inner walls having a ribbed lattice with longitudinal ribs and cross ribs defining panel supports around said combustion zone, said longitudinal ribs of said lattice having tracks formed therein, porous laminated panels slidably supported within said tracks for removable insertion therein, each of said panels serving to direct air from exteriorly of said outer and inner walls for cooling the inner surface of said outer and inner walls by transpiration cooling thereof.

2. A gas turbine engine combustor assembly comprising a plurality of support segments each including an outer wall and an inner wall, means joining said support segments to one another to form a continuously peripheral outer liner and inner liner defining an annular combustion zone therebetween, means for mixing and directing air and fuel into said combustion zone, each of said outer and inner walls having a ribbed lattice with longitudinal ribs and cross ribs defining panel supports around said combustion zone, said longitudinal ribs of said lattice having tracks formed therein, porous laminated panels slidably supported within said tracks for removable insertion therein, each of said panels serving to direct air from exteriorly of said outer and inner walls for cooling the inner surface of said outer and inner walls by transpiration cooling thereof, each of said panels being bowed outwardly of said combustion zone between said tracks to reinforce said panels against pressure differentials thereacross, each of said cross ribs having a curvature congruous with said panels and contacting said panels along their lengths for further reinforcement thereof.

3. A gas turbine engine combustor assembly comprising a plurality of support segments each including an outer wall and an inner wall, means joining said support segments to one another to form a continuously peripheral outer liner and inner liner defining an annular combustion zone therebetween, a dome on each of said joined support segments for forming an air fuel plenum upstream of said combustion zone, means for directing and mixing air and fuel within said plenum, a perforated header plate separating said plenum from said combustion zone for injecting streams of air and fuel mixture from said plenum into said combustion zone, each of said outer and inner walls having a ribbed lattice with longitudinal ribs and cross ribs defining panel supports around said combustion zone, said longitudinal ribs of said lattice having tracks formed therein, porous laminated panels slidably supported within said tracks for removable insertion therein, each of said panels serving to direct air from exteriorly of said outer and inner walls for cooling the inner surface of said outer and inner walls by transpiration cooling thereof.

4. A gas turbine engine combustor assembly comprising a plurality of support segments each including an outer wall and an inner wall, means joining said support segments to one another to form a continuously peripheral outer liner and inner liner defining an annular combustion zone therebetween, a dome on each of said joined support segments for forming an air fuel plenum upstream of said combustion zone, means for directing and mixing air and fuel within said plenum, a perforated header plate separating said plenum from said combustion zone for injecting streams of air and fuel mixture from said plenum into said combustion zone, each of said outer and inner walls having a ribbed lattice with longitudinal ribs and cross ribs defining panel supports around said combustion zone, said longitudinal ribs of said lattice having tracks formed therein, porous laminated panels slidably supported within said tracks for removable insertion therein, each of said panels serving to direct air from exteriorly of said outer and inner walls for cooling the inner surface of said outer and inner walls by transpiration cooling thereof, each of said panels being bowed outwardly of said combustion zone between said tracks to reinforce said panels against pressure differentials thereacross, each of said cross ribs having a curvature congruous with said panels and contacting said panels along their lengths for further reinforcement thereof.

5. An industrial gas turbine engine combustor assembly comprising a plurality of support segments each including an outer wall and an inner wall, means joining said support segments to one another to form a continuously peripheral outer liner and inner liner defining an annular combustion zone therebetween with an axial outlet, said liners being inclined upwardly from said axial outlet, a dome on each of said joined supports for forming an air fuel plenum upstream of said combustion zone, means for directing and mixing air and fuel within said plenum, a perforated header plate separating said plenum from said combustion zone for injecting streams of air and fuel mixture from said plenum into said combustion zone, each of said outer and inner walls having a ribbed lattice defining panels exteriorly of said combustion zone, said lattice having longitudinal ribs with tracks formed therein, porous laminated panels slidably supported within said tracks for removable insertion therein, each of said panels serving to direct air from exteriorly of said outer and inner walls for cooling the inner surface of said outer and inner walls by transpiration cooling thereof.