Axial stop configuration for a combustion liner
View Patent ↗An apparatus and method for mounting a combustion liner within a flow sleeve of a gas turbine combustion system is disclosed. A mounting system comprises a plurality of low-profile mounting tabs secured to a combustion liner where each of the mounting tabs are placed within slots of flow sleeve pegs when the combustion liner is installed in a flow sleeve. A plurality of liner stop brackets are removably secured to a flange of the flow sleeve and have an arm extending to be adjacent to a top contact surface of the mounting tabs. The mounting system reduces blockage to the surrounding airflow.
1. A mounting system for a gas turbine combustion system comprising:
a plurality of mounting tabs secured to a combustion liner, the mounting tabs having a top contact surface with a first width and a bottom contact surface with a second width;
a plurality of pegs secured to a flow sleeve, the plurality of pegs each having a slot configured to receive one of the plurality of mounting tabs;
a plurality of liner stop brackets secured to a flange of the flow sleeve and having an arm in contact with the top contact surface of the mounting tabs, at least one of the plurality of liner stop brackets comprising a bracket slot extending along a portion of the at least one of the plurality of liner stop brackets; and,
a combustor cap which resides at least partially within the bracket slot.
2. The mounting system of claim 1 , wherein the plurality of mounting tabs is equally spaced about the combustion liner.
3. The mounting system of claim 1 , wherein the plurality of mounting tabs is positioned proximate an inlet end of the combustion liner.
4. The mounting system of claim 1 , wherein the first width is greater than the second width.
5. The mounting system of claim 1 further comprising a recessed portion in the flange for receiving a first portion of the liner stop bracket.
6. The mounting system of claim 5 , wherein the liner stop brackets are bolted to the flange of the flow sleeve.
7. The mounting system of claim 1 further comprising a bracket slot in the arm of the liner stop brackets.
8. A method of securing a combustion liner in a flow sleeve of a gas turbine combustor comprising:
providing a flow sleeve having a plurality of flow sleeve pegs, with each flow sleeve peg having a slot;
providing a combustion liner having a plurality of mounting tabs extending away from an outer surface of the combustion liner;
inserting the combustion liner into the flow sleeve such that the plurality of mounting tabs is located within the slots of the plurality of flow sleeve pegs;
placing a liner stop bracket onto a flange of the flow sleeve such that the liner stop bracket holds the mounting tab, the liner stop bracket comprising a bracket slot extending along a portion of the liner stop bracket;
placing a portion of a combustor cap within the bracket slot; and,
securing the liner stop bracket to the flange of the flow sleeve.
9. The method of claim 8 , wherein the plurality of mounting tabs is positioned proximate an inlet end of the combustion liner.
10. The method of claim 8 , wherein the flange of the flow sleeve further comprises a plurality of holes.
11. The method of claim 10 further comprising a plurality of fasteners placed through the liner stop bracket and the flow sleeve for securing the liner stop bracket to the flange of the flow sleeve.
12. A mounting system for a gas turbine combustion system comprising:
a plurality of mounting tabs secured to a combustion liner, the mounting tabs having a top contact surface with a first width and a bottom contact surface with a second width that is less than the first width;
a plurality of pegs secured to a flow sleeve, the plurality of pegs each having a slot configured to receive one of the plurality of mounting tabs; and,
a plurality of liner stop brackets secured to a flange of the flow sleeve and having an arm in contact with the top contact surface of the mounting tabs, at least one of the plurality of liner stop brackets comprising a bracket slot extending along a portion of the at least one of the plurality of liner stop brackets; and,
a combustor cap which resides at least partially within the bracket slot.
13. The mounting system of claim 12 , wherein each of the plurality of liner stop brackets is removably secured to a recessed portion of the flange of the flow sleeve.
14. The mounting system of claim 13 , wherein each of the plurality of liner stop brackets is bolted to the recessed portion of the flange of the flow sleeve.
15. The mounting system of claim 14 , wherein each of the plurality of mounting tabs is positioned proximate an inlet end of the combustion liner.