Flow sleeve impingement cooling baffles
A combustor assembly for a turbine engine includes a combustor liner, a flow sleeve and a baffle ring. The flow sleeve surrounds the combustor liner. An annulus is formed between the flow sleeve and the combustor liner. A plurality of row of cooling holes are formed in the flow sleeve. The baffle ring radially surrounds the combustor liner and is located in the annulus.
1. A combustor assembly for a turbine engine, the combustor assembly comprising:
an annular combustor liner;
a flow sleeve surrounding the combustor liner;
a first annulus defined radially between the combustor liner and the flow sleeve;
a plurality of rows of cooling holes formed in the flow sleeve; and
a cooling baffle ring radially surrounding and spaced from the combustor liner in the first annulus for directing air onto the combustor liner, the baffle ring comprising:
a plurality of baffles extending radially inward, each baffle comprising: a pair of side walls, a pair of end walls, a bottom, and a first flow hole formed in the bottom; and
a plurality of lands.
2. The combustor assembly of claim 1 , wherein each baffle further comprises:
a second flow hole formed in the bottom of the baffle, wherein each baffle is aligned with a flow sleeve cooling hole so that air impinges on the combustor liner.
3. The combustor assembly of claim 2 wherein the first and second flow holes have a smaller diameter than the cooling hole with which the baffle is aligned.
4. The combustor assembly of claim 2 wherein the first and second flow holes have the same diameter as the cooling hole with which the baffle is aligned.
5. The combustor assembly of claim 2 , and further comprising:
a transition duct connected to the combustor liner;
an impingement sleeve connected to the flow sleeve and radially surrounding the transition duct; and
a second flow annulus radially defined between the transition duct and the impingement sleeve, wherein the baffle ring is positioned in the first flow annulus adjacent to the transition duct for directing air from the second flow annulus to the first flow annulus, and for directing air onto the combustor liner.
6. The combustor assembly of claim 5 , wherein the first flow holes are aligned with a first row of cooling holes adjacent the impingement sleeve.
7. The combustor assembly of claim 5 , wherein the first flow hole has a first flow hole diameter and the second flow hole has a second flow hole diameter, and wherein the first flow hole diameter is smaller than the second flow hole diameter.
8. The combustor assembly of claim 7 , wherein the first flow holes are aligned with a first row of cooling holes adjacent the impingement sleeve.
9. The combustor assembly of claim 5 , wherein each baffle has an upstream portion adjacent the impingement sleeve and a downstream portion opposite the upstream portion, and wherein the first flow hole is in the upstream portion and the second flow hole is in the downstream portion, and wherein the first flow hole is closer to the combustor liner than the second flow hole.
10. The combustor assembly of claim 9 , wherein the first flow hole has a first flow hole diameter and the second flow hole has a second flow hole diameter, and wherein the first flow hole diameter is smaller than the second flow hole diameter.
11. The combustor assembly of claim 1 , wherein the baffle ring is a one-piece assembly.
12. A method of cooling an annular combustor liner, the method comprising:
surrounding the annular combustor liner with a flow sleeve so that a flow annulus is formed between the combustor liner and the flow sleeve, wherein the flow sleeve includes a first row of cooling holes; and
radially surrounding the combustor liner with a baffle ring spaced from the combustor liner, wherein the baffle ring comprises a plurality of baffles extending in a radially inward direction, each baffle comprising: a pair of side walls, a pair of end walls, a bottom, and a first flow hole formed in the bottom, and wherein the first flow hole is aligned with the first row of cooling holes; and
directing impingement air through the baffle ring onto the combustor liner.
13. The method of claim 12 wherein each cooling hole has a larger diameter than the first flow hole with which it is aligned.
14. The method of claim 12 , and further comprising forming a second flow hole in each baffle, wherein the first flow hole has a first flow hole diameter and the second flow hole has a second flow hole diameter, and wherein the first flow hole diameter is smaller than the second flow hole diameter.
15. The method of claim 14 wherein the first flow hole is closer to the combustor liner than the second flow hole.
16. The method of claim 12 , wherein the baffle ring is a one-piece assembly.