Patent Grant
8291711
The present invention relates to a combustor assembly of a gas turbine engine. More specifically, the present invention relates to an apparatus and method of cooling a combustor liner of a gas turbine engine.
A gas turbine engine extracts energy from a flow of hot combustion gases. Compressed air is mixed with fuel in a combustor assembly of the gas turbine engine, and the mixture is ignited to produce hot combustion gases. The hot gases flow through the combustor assembly and into a turbine where energy is extracted.
Conventional gas turbine engines use a plurality of combustor assemblies. Each combustor assembly includes a fuel injection system, a combustor liner and a transition duct. Combustion occurs in the combustion liner. Hot combustion gases flow through the combustor liner and the transition duct into the turbine.
The combustor liner, transition duct and other components of the gas turbine engine are subject to these hot combustion gases. Current design criteria require that the temperature of the combustor liner be kept within its design parameters by cooling it. One way to cool the combustor liner is impingement cooling a surface wall of the liner.
In impingement cooling of a combustor liner, the front side (inner surface) of the combustor liner is exposed to the hot gases, and a jet-like flow of cooling air is directed towards the backside wall (outer surface) of the combustor liner. After impingement, the “spent air” (i.e. air after impingement) flows generally parallel to the component.
Gas turbine engines may use impingement cooling to cool combustor liners and transition ducts. In such arrangements, the combustor liner is surrounded by a flow sleeve, and the transition duct is surrounded by an impingement sleeve. The flow sleeve and the impingement sleeve are each formed with a plurality of rows of cooling holes.
A first flow annulus is created between the flow sleeve and the combustor liner. The cooling holes in the flow sleeve direct cooling air jets into the first flow annulus to impinge on the combustor liner and cool it. After impingement, the spent air flows axially through the first flow annulus in a direction generally parallel to the combustor liner.
A second flow annulus is created between the transition duct and the impingement sleeve. The holes in the impingement sleeve direct cooling air into the second flow annulus to impinge on the transition duct and cool it. After impingement, the spent air flows axially through the second flow annulus.
The combustor liner and the transition duct are connected, and the flow sleeve and the impingement sleeve are connected, so that the first flow annulus and the second flow annulus create a continuous flow path. That is, spent air from the second flow annulus continues into the first flow annulus. This flow from the second flow annulus creates cross flow effects on cooling air jets of the flow sleeve and may reduce the effectiveness and efficiency of these cooling air jets. For example, flow through the second flow annulus may bend the jets entering through the flow sleeve, reducing the heat transferring effectiveness of the jets or completely preventing the jets from reaching the surface of the combustor liner. This is especially a problem with regard to the first row of flow sleeve cooling holes adjacent the impingement sleeve.
A combustor assembly for a turbine includes a combustor liner surrounded by a flow sleeve formed with a plurality of holes. A first flow annulus is formed between the combustor liner and the flow sleeve. Hot combustion gases flow through the combustor liner to a turbine. The combustor liner must be cooled to keep its temperature with the design specifications. One technique to cool the combustor liner is impingement cooling.
The baffle ring radially surrounds the combustor liner and is located in the annulus. The baffle ring directs air onto the combustor liner to cool it. The baffle ring may be added to a new or existing gas turbine assembly to provide efficient cooling flow to the combustor liner and improve impingement cooling. Compared to other impingement assemblies, the baffle ring has a reduced the part-count, lower cost, and a reduced potential for foreign object damage in the combustor assembly.
Flow sleeve 14 surrounds combustor liner 12 and is formed with a plurality of rows of cooling holes 24A, 24B, 24C, 24D (generally referred to as cooling holes 24). First flow annulus 26 is formed between combustor liner 12 and flow sleeve 14. Cooling air enters as jet-like flow into first flow annulus 26 through cooling holes 24, and impinges upon combustor liner 12 to cool it. After impingement, the spent cooling air flows generally parallel to combustor liner 12 in first flow annulus 26. The flow of spent cooling air through first flow annulus 26 is indicated by arrow 27.
Impingement sleeve 18 surrounds transition duct 16. Second flow annulus 28 is formed between transition duct 16 and impingement sleeve 18. Impingement sleeve 18 is formed with a plurality of rows of cooling holes 30. Similar to the impingement of combustor liner 12, cooling air enters second flow annulus 28 through cooling holes 30 and impinges upon transition duct 16 to cool it. After impingement, the spent cooling air flows generally parallel to transition duct 16 in second flow annulus 28. The flow of spent cooling air through second flow annulus 28 is indicated by arrow 29.
Combustor liner 12 and transition duct 16 are connected by sliding seal 34. Flow sleeve 14 and impingement sleeve 18 are connected at sliding joint and piston (seal) ring 32 so that first flow annulus 26 and second flow annulus 28 create a continuous flow path. After impingement on transition duct 16, spent cooling air from second flow annulus 28 continues downstream into first flow annulus 26.
The flow of spent cooling air 27, 29 is opposite the flow of hot gases 20 through combustor liner 12. Therefore, the terms “upstream” and “downstream” depend on which flow of air is referenced. In this application, the terms “upstream” and “downstream” are determined with respect to the flow of spent cooling air 27, 29.
Baffle ring 36 includes a plurality of lands 38 and baffles 40. Baffles 40 extend radially inwards towards combustor liner 12 so that the cooling air flow is closer to combustor liner 12 and the cross flow effects are decreased. In one example, baffle ring 36 is about 25% longer than baffles 40. Lands 38 are located between baffles 40. Lands 38 provide passage for air flow from second flow annulus 28. Baffles 40 and lands 38 may be the same width or may be different widths. In one example, baffles 40 are about one third wider than lands 38.
Baffle ring 36 lies in first flow annulus 26 and surrounds a section of combustor liner 12. Baffle ring 36 is sized to fit against the inner surface of flow sleeve 14 so that lands 38 are in contact with flow sleeve 14.
Baffle ring 36 may be attached to flow sleeve 14 by mechanical fastening means. In one example, two rows of rivets 39 may attach baffle ring 36 to flow sleeve 14. In another example, baffle ring 36 may be welded to flow sleeve 14.
Baffle ring 36 is formed so that when baffle ring 36 is in place, baffles 40 align with cooling holes 24 and lands 38 do not align with cooling holes 24. In use, cooling air flows through cooling holes 24 into baffles 40, and impinges on combustor liner 12. Lands 38 fit against the inner surface of flow sleeve 14. Lands 38 provide flow passage through first flow annulus 26. Lands 38 do not block the air flow from second flow annulus 28 into first flow annulus 26. This prevents a pressure drop between annulus 26 and annulus 28.
Sections 50, 52, and 54 may be the same length or may be different lengths. In one example, upstream section 50 is longer than downstream section 52, and downstream section 52 is longer than transition section 54.
At least one baffle cooling hole 56A is formed in each baffle bottom 48. In one example, baffle cooling holes 56A, 56B may be formed in each baffle 40. Baffle cooling holes 56A, 56B (referred to generally as baffle cooling holes 56) may be aligned with cooling holes 24. In one example, baffle cooling hole 56A is aligned with cooling hole 24A and baffle cooling hole 56B is aligned with cooling hole 24B, where cooling hole 24A is adjacent to impingement sleeve 18 and cooling hole 24B is adjacent to cooling hole 24A.
The diameters of baffle cooling holes 56A, 56B depends on the desired cooling flow rate. Larger baffle cooling holes 56A, 56B provide more cooling air to combustor liner 12. The diameter of baffle cooling holes 56A may be the same or different than baffle cooling hole 56B. In one example, baffle cooling hole 56A has a smaller diameter than baffle cooling hole 56B. In another example, baffle cooling hole 56B is about 45% larger in diameter than baffle cooling hole 56A. In another example, baffle cooling hole 56A has a diameter of 0.52 about inches (1.3 cm) and baffle cooling hole 56B has a diameter of about 0.75 inches (1.9 cm).
The diameters of cooling holes 24 may be the same as or may be larger than the diameters of baffle cooling holes 56. In one example, the diameters of cooling holes 24 are larger than the diameters of the baffle cooling holes 56 with which they are aligned so that the smaller baffle cooling holes 56 set the flow resistance and meter the cooling air flowing into first flow annulus 26.
In order to extend between baffle bottom 48 of upstream section 50 and baffle bottom 48 of downstream section 52 when upstream section 50 and downstream section 52 have different depths, baffle bottom 48 of transition section 54 must be at an angle. In one example, baffle bottom 48 of transition section 54 is at about a thirty degree angle to baffle bottom 48 of upstream section 50.
The depth of baffle 40 affects the distance between baffle bottom 48 and combustor liner 12. The greater the depth, the closer baffle bottom 48 is to combustor liner 12. Therefore, baffle bottom 48 of upstream section 50 may be closer to or farther away from combustor liner 12 than baffle bottom 48 of downstream section 52. In one example, baffle bottom 48 of upstream section 50 is closer to combustor liner 12 than baffle bottom 48 of downstream section 52.
Baffle 40 extends into first flow annulus 26 and guides cooling air jets G and J, ensuring that combustor liner 12 is impinged at the desired point. End wall 46A deflects air flow F downward so that the air flows between baffle bottom 48 and combustor liner 12.
As discussed above, upstream section 50 of baffle 40 may be deeper or the baffle bottom 48 of upstream section 50 may be closer to combustor liner 12 than downstream section 52. In this arrangement, upstream section 50 of baffle 40 blocks the cross flow for downstream section 52. Therefore, downstream section 52 does not encounter as much cross flow as upstream section 50 and it is not necessary for downstream section 52 to be as close to combustor liner 12.
Baffle ring 36 is a one-piece assembly. In contrast, prior art assemblies inserted a plurality of individual tubes or conduits into cooling holes 24. In one prior art assembly as many as 48 individual tubes were welding into cooling holes 24. This is expensive and labor intensive. The large number of pieces also increases the probability that a piece will come loose and cause damage to downstream turbine blades and vanes. This is known as foreign object damage (FOD). Baffle ring 36 reduces part count, decreases cost and reduces FOD potential.
Although the present invention has been described with reference to preferred embodiments, workers skilled in the art will recognize that changes may be made in form and detail without departing from the spirit and scope of the invention. For example, although baffle ring 36 has been described as being part of a new combustor assembly, baffle ring may be added to an existing combustor assembly to provide a more efficient cooling flow to the liner and improve impingement cooling.
| Number | Name | Date | Kind |
|---|---|---|---|
| 4339925 | Eggmann et al. | Jul 1982 | A |
| 5363654 | Lee | Nov 1994 | A |
| 5388412 | Schulte-Werning et al. | Feb 1995 | A |
| 5467815 | Haumann et al. | Nov 1995 | A |
| 5533864 | Nomoto et al. | Jul 1996 | A |
| 5586866 | Wettstein | Dec 1996 | A |
| 5782294 | Froemming et al. | Jul 1998 | A |
| 6000908 | Bunker | Dec 1999 | A |
| 6484505 | Brown et al. | Nov 2002 | B1 |
| 6701714 | Burd et al. | Mar 2004 | B2 |
| 6711900 | Patel et al. | Mar 2004 | B1 |
| 6810673 | Snyder | Nov 2004 | B2 |
| 6837053 | Tiemann | Jan 2005 | B2 |
| 6925808 | Tiemann | Aug 2005 | B2 |
| 7270175 | Mayer et al. | Sep 2007 | B2 |
| 7278256 | Norris et al. | Oct 2007 | B2 |
| 7707835 | Lipinski et al. | May 2010 | B2 |
| Number | Date | Country | |
|---|---|---|---|
| 20100031666 A1 | Feb 2010 | US |
