초록 ▼

A two-stage gas turbine combustor is disclosed that incorporates an improved assembly and disassembly methodology that results in improved inspection and repair techniques. The combustor includes an upper liner, lower liner, cap assembly, and a venturi assembly that directs cooling air into the comb

A two-stage gas turbine combustor is disclosed that incorporates an improved assembly and disassembly methodology that results in improved inspection and repair techniques. The combustor includes an upper liner, lower liner, cap assembly, and a venturi assembly that directs cooling air into the combustion chamber for use in the combustion process, wherein a venturi assembly is inserted within an upper liner and an upper liner is then inserted in a lower liner. The venturi assembly, upper liner, and lower liner are fixed together with a plurality of easily removable retaining pins. The improved assembly allows for easier inspection and repair of the upper liner, lower liner, and venturi assembly.

대표청구항 ▼

1. A gas turbine combustor having a first combustion chamber in fluid communication with a second combustion chamber, said combustor comprising:a venturi assembly comprising: a first venturi end proximate said first combustion chamber and a second venturi end proximate said second combustion chamber

1. A gas turbine combustor having a first combustion chamber in fluid communication with a second combustion chamber, said combustor comprising:a venturi assembly comprising: a first venturi end proximate said first combustion chamber and a second venturi end proximate said second combustion chamber; a flowpath wall extending from said first venturi end to said second venturi end and having a first outer band, first convergent wall, first divergent wall, said first convergent wall abutting said first divergent wall at a first throat, a first annular wall extending from said first divergent wall, and a blocking ring fixed to said first annular wall, said first outer band having a first band diameter, a second band diameter, and a first thickness therebetween, said first throat positioned axially between said first and second combustion chambers; a passageway wall having a second convergent wall, a second divergent wall, and a second annular wall in spaced relation to and radially outward of said flowpath wall thereby forming a first passageway there between; a plurality of first holes spaced circumferentially about said first outer band, said first holes in fluid communication with said first passageway; an upper liner generally annular in shape having a first upper end, a second upper end, a first upper diameter, and a second upper diameter, said first upper diameter and said second upper diameter proximate said second upper end defining a second thickness there between, a plurality of second holes circumferentially spaced about said upper liner and in fluid communication with said first holes and a second passageway radially outward of said upper liner; a lower liner generally annular in shape having a first lower end, a second lower end, a first lower diameter, and a second lower diameter, said first lower diameter and said second lower diameter proximate said first lower end defining a third thickness there between, a plurality of third holes circumferentially spaced about said lower liner proximate said second venturi end, said third holes in fluid communication with said first passageway; and, a cap assembly for securing a plurality of fuel nozzles to said combustor, said cap assembly fixed to said upper liner proximate said first upper end; wherein said venturi assembly is secured to said upper liner and said lower liner in an easily removable manner by a plurality of retaining pins such that said first outer band of said venturi is located radially within said upper liner and said upper liner is located radially within said lower liner. 2. The gas turbine combustor of claim 1 wherein said second band diameter is only slightly less than said first upper diameter.3. The gas turbine combustor of claim 1 wherein said second upper diameter is only slightly less than said first lower diameter.4. The gas turbine combustor of claim 1 wherein said first venturi end is in contact with said upper liner.5. The gas turbine combustor of claim 1 wherein said plurality of retaining pins comprise at least six retaining pins.6. The gas turbine combustor of claim 1 wherein each of said plurality of retaining pins passes through said lower liner, said upper liner, and said first outer band.7. The gas turbine combustor of claim 1 wherein said lower liner is intermittently welded to said upper liner proximate said plurality of retaining pins.8. A method of assembling a gas turbine combustor having a first combustion chamber in fluid communication with a second combustion chamber comprising the steps:providing a venturi assembly comprising: a first venturi end proximate said first combustion chamber and a second venturi end proximate said second combustion chamber; a flowpath wall extending from said first venturi end to said second venturi end and having a first outer band, first convergent wall, first divergent wall, said first convergent wall abutting said first divergent wall at a first throat, a first annular wall extending from said first divergent wall, and a blocking ring fixed to said first annular wall, said first outer band having a first band diameter, a second band diameter, and a first thickness there between, said first throat positioned axially between said first and second combustion chambers; a passageway wall having a second convergent wall, a second divergent wall, and a second annular wall in spaced relation to and radially outward of said flowpath wall thereby forming a first passageway there between; a plurality of first holes spaced circumferentially about said first outer band, said first holes in fluid communication with said first passageway; providing an upper liner generally annular in shape having a first upper end, a second upper end, a first upper diameter, and a second upper diameter, said first upper diameter and said second upper diameter proximate said second upper end defining a second thickness therebetween, a plurality of second holes circumferentially spaced about said upper liner and in fluid communication with said first holes and a second passageway radially outward of said upper liner; providing a lower liner generally annular in shape having a first lower end, a second lower end, a first lower diameter, and a second lower diameter, said first lower diameter and said second lower diameter proximate said first lower end defining a third thickness there between, a plurality of third holes circumferentially spaced about said lower liner proximate said second venturi end, said third holes in fluid communication with said first passageway; providing a cap assembly for securing a plurality of fuel nozzles to said combustor; inserting said venturi assembly into said upper liner at said second upper end; inserting said upper liner into said lower liner at said first lower end; securing said venturi assembly to said upper liner and said lower liner with a plurality of retaining pins spaced circumferentially about said combustor; and, securing said cap assembly to said upper liner proximate said first upper end. 9. The method of assembling a gas turbine combustor according to claim 8 wherein said plurality of retaining pins comprise at least six retaining pins.10. The method of assembling a gas turbine combustor according to claim 8 wherein each of said plurality of retaining pins passes through at least said lower liner, said upper liner, and said first outer band.11. The method of assembling a gas turbine combustor according to claim 8 further comprising the step of intermittently welding said lower liner to said upper liner proximate said retaining pins after said venturi assembly is secured to said upper liner and said lower liner with said retaining pins.