Title of Invention

"COOLING CIRCUITS FOR A GAS TURBINE STATIONARY RING"

Abstract

A stationary ring (4) surrounding a hot gas passage (14) of a gas turbine (1), said ring (4) being surrounded by a stationary annular housing (2) so as to co-operate 5 therewith to define an annular cooling chamber (26) into which there opens out at least one cooling air feed orifice (28), said ring (4) being made up of a plurality of ring segments (16), the ring being characterized in that each ring segment (16) includes a top internal cooling circuit (A) and a bottom internal cooling circuit (B, B'), said bottom cooling circuit (B, B') being independent of said top cooling circuit (A), being radially offset relative to said top cooling circuit (A), and including at least one cooling air feed orifice (48) leading from the cooling chamber (26). Fig. 2

Full Text

Title of the invention Cooling circuits for a gas turbine stationary ring Background of the invention The present invention relates to stationary rings surrounding gas passages in a gas turbine, and more particularly it relates to cooling stationary rings in a gas turbine. A gas turbine, in particular a high pressure turbine of a turbomachine, typically comprises a plurality of stationary vanes alternating with a plurality of moving blades in the passage for hot gas coming from the combustion chamber of the turbomachine. The moving blades on the turbine are surrounded over their entire circumference by a stationary ring that is generally made up of a plurality of ring segments. These ring segments define part of the flow passage for hot gas passing through the blades of the turbine. The ring segments of the turbine are thus subjected to the high temperatures of the hot gas coming from the combustion chamber of the turbomachine. To enable the turbine ring to withstand the temperature and mechanical stresses to which it is subjected, it is necessary to provide the ring segments with cooling devices. One of the known methods of cooling consists in feeding cooling air to an impact plate mounted on the bodies of the ring segments. The plate is provided with a plurality of orifices for passing air which, under the pressure difference between the sides of the plate, comes to cool the ring segment by impact. The cooling air is then exhausted into the hot gas passage via holes formed through the ring segment. Such a method does not enable effective and uniform cooling of the ring segments to be obtained, particularly at the upstream ends of the ring segments which constitute a zone that is particularly exposed to hot gas. This therefore has an affect on the lifetime of the ring segment. Furthermore, that technology requires too great an amount of cooling air to be taken, thereby decreasing the performance of the turbine. Object and brief summary of the invention The present invention thus seeks to mitigate such drawbacks by proposing a stationary ring for a gas turbine in which each ring segment is provided with internal cooling circuits that require only a small flow of air, and enabling the ring segment to be cooled effectively by thermal convection. To this end, the invention provides a stationary ring surrounding a hot gas passage of a gas turbine, the ring being surrounded by a stationary annular housing so as to co-operate therewith to define an annular cooling chamber into which there opens out at least one cooling air feed orifice, the ring being made up of a plurality of ring segments, the ring being characterized in that each ring segment includes a top internal cooling circuit and a bottom internal cooling circuit, the bottom cooling circuit being independent of the top cooling circuit and being radially offset relative to the top cooling circuit. The top and bottom internal cooling circuits benefit from high heat exchange coefficients in order to provide effective and uniform cooling of each ring segment. These circuits make it possible in particular to cool the ring segment zones that are the most exposed to the hot gas. It is thus possible to reduce the air flow needed for cooling the ring segments, even under severe thermodynamic conditions of turbine operation. As a result, the lifetime of the stationary ring of the turbine can be increased and the performance of the turbine is little affected by the air that is taken for cooling the ring segments. The top cooling circuit serves in particular to cool the upstream end of the ring segment and to improve the effectiveness of the bottom cooling circuit. The bottom cooling circuit serves to cool the inside surface of the ring segment, and possibly of the adjacent ring segments. The top and bottom internal cooling circuits are independent of each other, which presents the advantages of enabling the cooling that is performed by each cooling circuit to be independent and of enabling the air flow fed to each circuit to be adapted thereto. For example, a large flow could be used for the top circuit in order to cool the upstream end of the ring segment effectively (i.e. the hottest zone thereof), while a smaller flow could be used for the bottom circuit. The independence between the cooling circuits also makes it possible to optimize cooling in independent manner. Brief description of the drawings Other characteristics and advantages of the present invention appear from the following description given with reference to the accompanying drawings which show an embodiment that has no limiting character. In the figures: • Figure 1 is a diagram of a portion of a gas turbine showing the location of a stationary ring relative to the location of the moving blades; • Figure 2 is a longitudinal section view of a ring segment in an embodiment of the invention; • Figures 3 and 4 are two respective section views on planes III-III and IV-IV of Figure 2; • Figure 5 is a longitudinal section view of a ring segment in another embodiment of the invention; and • Figure 6 is a section view on VI-VI of Figure 5. Detailed description of an embodiment Reference is made initially to Figure 1 which is a diagram showing a portion of a high pressure turbine 1 of a turbomachine. The high pressure turbine 1 includes in particular a stationary annular housing 2 constituting a casing of the turbomachine. A stationary turbine ring 4 is secured to the housing 1 and surrounds a plurality of moving blades 6 of the turbine. These moving blades 6 are disposed downstream from stationary vanes 8 relative to the flow direction 10 of the hot gas coming from a combustion chamber 12 of the turbomachine and passing through the turbine. Thus, the ring 4 of the turbine surrounds a flow passage 14 for hot gas. In general, the turbine ring 4 comprises a plurality of ring segments disposed circiimferentially around the axis of the turbine (not shown) so as to form a continuous circular surface. Nevertheless, it is also possible for the turbine ring to be constituted by a single continuous part. The present invention applies equally well to a single turbine ring and to a segment of a turbine ring. With reference to Figure 2, it can be seen that each ring segment 16 forming the stationary ring presents an inner annular surface 18 and an outer annular surface 20 that is radially offset relative to the inner surface 18. The inner surface 18 faces the hot gas flow passage 14. Each ring segment 16 also presents, at its upstream transverse wall 16a, an upstream hook 22, and at its downstream transverse wall 16b, a downstream hook 24. The upstream and downstream hooks 22 and 24 enable the ring segment 16 to be secured to the stationary annular housing 2 of the turbine. The stationary annular housing 2 and the turbine ring made up of the ring segments 16 define between them an annular cooling chamber 2 6 that is fed with cooling air via at least one orifice 28 passing through the stationary annular housing 2. The cooling air feeding this cooling chamber 2 6 typically comprises a fraction of the outside air passing through a fan and flowing around the combustion chamber of the turbomachine. According to the invention, each ring segment 16 is provided with a top internal cooling circuit A and a bottom internal cooling circuit B, B', the bottom cooling circuit B, B' being independent of the top cooling circuit A and being radially offset relative thereto. These top and bottom cooling circuits A and B, B' serve to cool the ring segments by thermal convection. More precisely, the top cooling circuit A is for cooling the outer annular surface 2 0 and the upstream end of the ring segment 16 which is the end of ring segment that is the most exposed to hot gas. The bottom cooling circuit B, B' serves to cool the inner annular surface 18 of the ring segment 16 which is the surface that is the most exposed to the stream of hot gas. The top cooling circuit A also makes it possible to improve the efficiency of the cooling performed by the bottom circuit B, B' . An embodiment of the ring segment of the invention is described below with reference to Figures 2 to 4. In these figures the top cooling circuit A comprises at least a first internal cavity 32 which extends circumferentially between longitudinal walls 16c, 16d of the ring segment 16. This first cavity 32 also extends over a fraction only of the axial length of the ring segment 16 defined between its upstream and downstream transverse walls 16a and 16b. The top cooling circuit A also has at least one second internal cavity 34 extending circumferentially between the longitudinal walls 16c and 16d of the ring segment 16. This second cavity 34 is disposed axially upstream from the first cavity 32, i.e. between the upstream transverse wall of the first cavity 32 and the upstream transverse wall 16a of the ring segment 16. The axial length of the second cavity 34 (i.e. the distance between its transverse walls) is substantially smaller than that of the first cavity 32. At least one cooling air feed orifice 3 6 leads from the cooling chamber 2 6 into the first cavity 32 in order to feed the top circuit A with cooling air. More precisely, this feed orifice 3 6 leads from the cooling chamber 26 into the downstream end of the first cavity 32. A plurality of emission holes 38 are also provided leading from the first cavity 32 into the second cavity 34. These emission holes 38 enable the second cavity 34 to be cooled by air impact. The top cooling circuit A also includes a plurality of outlet holes 40a, 40b leading from the second cavity 34 into the hot gas passage 14 at the upstream end of the ring segment 16. The cooling air flowing in the top circuit A is thus exhausted via these outlet holes 40a, 40b. More precisely, a first series of outlet holes 40a is provided opening out into the hot gas passage 14 at the inner annular surface 18 of the ring segment 16, and a second series of outlet holes 40b is provided that open out into the hot gas passage 14 at the upstream transverse wall 16a of the ring segment. For this purpose, the outlet holes 40a in the first series may be inclined relative to the flow direction 10 of the hot gas, while the outlet holes 40b of the second series may be substantially parallel to said flow direction. Naturally, it would also be possible for the top cooling circuit A to present other series of outlet holes opening out into the hot gas passage, at the upstream end of the ring segment 16. It should also be observed that in Figure 3 the outlet holes 40a and 40b are substantially in alignment on an axial direction relative to the emission holes 38 leading from the first cavity 32 into the second cavity 34. Such a disposition serves to reduce head losses. Nevertheless, it would also be possible for the outlet holes 40a and 40b not to be in alignment with the emission holes 38. In the embodiment shown in Figures 2 to 4, the bottom internal cooling circuit B is provided with at least three internal cavities 42, 44, and 46 which extend circumferentially between the longitudinal walls 16c and 16d of the ring segment 16. These three cavities 42, 44, and 46 are also radially offset relative to the first cavity 32 of the top cooling circuit A, i.e. they are disposed between the first cavity 32 of the top circuit A and the internal annular surface 18 of the ring segment 16. More precisely, at least one first internal cavity 42 is disposed on the downstream end of the ring segment 16. At least one second internal cavity 44 is disposed axially upstream from the first cavity 42. Similarly, at least one third internal cavity 46 is disposed axially upstream from the second cavity 44. It should be observed in Figures 2 and 4 that these three cavities 42, 44, and 46 are of axial lengths (i.e. the distance between their respective transverse walls) that are substantially identical and that they are spaced apart from one another at substantially equivalent distances. The bottom cooling circuit B is fed with cooling air via at least one feed orifice 48 leading from the cooling chamber 26 into the first cavity 42. The bottom cooling circuit B also has at least one first passage 50 putting the first cavity 42 into communication with the second cavity 44, and at least one second passage 52 putting the second cavity 44 into communication with the third cavity 46. A plurality of outlet holes 54 lead from the third cavity 46 into the hot gas passage 14, at the upstream end of the ring segment 16 for the purpose of cooling it. The outlet holes 54 open out in the upstream end of the ring segment, through the internal annular surface 18 thereof. By way of example they are inclined relative to the flow direction 10 of the hot gas. The cooling air flowing in the bottom circuit B is thus exhausted via the outlet holes 54. The second cavity 44 of the bottom cooling circuit B is preferably provided with baffles 56 so as to increase heat transfer. As shown in Figure 4, these baffles 56 may be splines extending longitudinally perpendicularly to the air flow direction in the second cavity 44. These baffles may also take the form of studs or bridges, for example. Advantageously, the air feed orifice 48 and the second passage 52 of the bottom circuit B are disposed beside one of the longitudinal walls 16c (or 16d) of the ring segment 16, while the first passage 50 of the bottom circuit B is disposed beside the other longitudinal wall 16d (or 16c) of the ring segment. Such a disposition enables the cooling air flow path within the bottom circuit B to be lengthened so as to increase heat transfer. Another embodiment of the ring segment of the invention is described below with reference to Figures 5 and 6. In this embodiment, the top cooling circuit A of the ring segment is identical to that described above. However the bottom cooling circuit B' is different. The bottom cooling circuit B' comprises at least four internal cavities 58, 60, 62, and 64 which extend axially between the upstream and downstream transverse walls 16a and 16b of the ring segment 16. These four cavities 58, 60, 62, and 64 are also radially offset relative to the first cavity 32 of the top cooling circuit A, i.e. they are disposed between the first cavity 32 of the top circuit A and the internal annular surface 18 of the ring segment 16. The first cavity 58 of this bottom cooling circuit B' is disposed beside one of the longitudinal walls 16c (or 16d) of the ring segment 16. The second cavity 60 is offset circumferentially relative to the first cavity 58, the third cavity 62 is offset circumferentially relative to the second cavity, and the fourth cavity 64 is offset circumferentially relative to the third cavity. These cavities are disposed in such a manner that the fourth cavity 64 is disposed beside the longitudinal wall 16d (or 16c) opposite from the wall beside the first cavity 58. At least first and second cooling air feed orifices 66 and 68 lead from the cooling chamber 26 into the second and third cavities 60 and 62 respectively in order to feed them with cooling air. The bottom cooling circuit B' also has at least one first passage 70 putting the second cavity 60 into communication with the first cavity 58. Similarly, at least one second passage 72 puts the third cavity 62 into communication with the fourth cavity 64. Finally, the bottom cooling circuit B' is provided with at least one plurality of first outlet holes 74 leading from the first cavity 58 into the hot gas passage 14 via the longitudinal wall 16c of the ring segment 16 located beside the first cavity 58. Similarly, at least one plurality of second outlet holes 76 is provided leading from the fourth cavity 64 into the hot gas passage 14 via the other longitudinal wall 16b of the ring segment 16. As a result, two mutually dependent bottom sub-circuits are obtained. As shown in Figure 6, these sub-circuits may be substantially symmetrical relative to a middle longitudinal axis of the ring segment. These bottom sub-circuits are fed independently via the feed orifices 66 and 68, and they present independent outlet holes 74 and 76, serving to cool the ring segments adjacent to the ring segment in question. The second and third cavities 60 and 62 of the bottom cooling circuit B' preferably include respective baffles 78 so as to increase heat transfer. These baffles 78 may be in the form of transversely-extending ribs (as in Figures 5 and 6), or of studs, or indeed of bridges. Furthermore, the first and second feed orifices 66 and 68 of the bottom circuit B' are advantageously formed beside one of the transverse walls 16a, 16b of the ring segment 16 (in Figure 6 beside the downstream wall 16b), and the first and second passages 7 0 and 72 of the bottom circuit B' are formed beside the other transverse wall 16b or 16a of the ring segment 16 (in Figure 6 beside the upstream wall 16a). This disposition serves to increase the cooling air flow path through the second bottom circuit B' in order to increase heat transfer. We claim: 1. A stationary ring (4) surrounding a hot gas passage (14) of a gas turbine (1), said ring (4) being surrounded by a stationary annular housing (2) so as to co-operate 5 therewith to define an annular cooling chamber (26) into which there opens out at least one cooling air feed orifice (28), said ring (4) being made up of a plurality of ring segments (16), the ring being characterized in that each ring segment (16) includes a top internal cooling circuit (A) and a bottom internal cooling circuit (B, B'), said bottom cooling circuit (B, B') being independent of said top cooling circuit (A), being radially offset relative to said top cooling circuit (A), and including at least one cooling air feed orifice (48) leading from the cooling chamber (26). 2. A ring (4) as claimed in claim 1, wherein said top cooling circuit (A) of each ring segment (16) comprises: at least one first internal cavity (32) extending circumferentially between the longitudinal walls (16c, 16d) of said ring segment (16); at least one second internal cavity (34) extending circumferentially between the longitudinal walls (16c, 16d) of said ring segment (16) and disposed axially upstream from said first cavity; at least one cooling air feed orifice (36) leading from the cooling chamber (26) and into said first cavity (32) in order to feed said first cavity; a plurality of emission holes (38) leading from said first cavity (32) into said second cavity (34) so as to cool said second cavity (34) by air impact; and a plurality of outlet holes (40a, 40b) leading from said second cavity (34) and into the hot gas passage (14) at the upstream end of said ring segment (16). 3. A ring (4) as claimed in claim 1 or claim 2, wherein said bottom cooling circuit (B) of each ring segment (16) comprises: at least one first internal cavity (42) extending 5 circumferentially between the longitudinal walls (16c, 16d) of said ring segment (16) and disposed at the downstream end of said ring segments; at least one second internal cavity (44) extending circumferentially between the longitudinal walls (16c, 16d) of said ring segment (16) and disposed axially upstream from said first cavity; at least one third internal cavity (46) extending circumferentially between the longitudinal walls (16c, 16d) of said ring segment (16) and disposed axially upstream from said second cavity (44); at least first and second passages (50, 52) respectively putting said first cavity (42) into communication with said second cavity (44), and said second cavity (44) into communication with said third cavity (46); and a plurality of outlet holes (54) leading from said third cavity (46) into the hot gas passage (14) at the upstream end of said ring segment (16), the cooling air feed orifice (48) leading into the first cavity (42) in order to feed it with air. 4. A ring (4) as claimed in claim 3, wherein said second internal cavity (44) of the bottom cooling circuit (B) is provided with baffles (56) so as to increase heat transfer. 5. A ring (4) as claimed in claim 2 or claim 3, wherein said air feed orifice (48) and said second passage (52) of the bottom cooling circuit (13) are formed beside one of the longitudinal walls (16c, 16d) of the ring segment (16), and said first passage (50) of the bottom cooling circuit (B) is formed beside the other longitudinal wall (16d, 16c) of the ring segment (16) in such a manner as to increase the cooling air flow path length. 6. A ring (4) as claimed in claim 1 or claim 2, wherein said bottom circuit cooling (B') of each ring segment (16) comprises: at least one fist internal cavity (58) extending axially between upstream and downstream transverse walls 10 (16a, 16b) of said ring segment (16) and disposed beside one of the longitudinal walls (16c, 16d) of said ring segment (16); at least one second internal cavity (60) extending axially between the upstream and downstream transverse walls (16a, 16b) of said ring segment (16) and circumferentially offset relative to said first cavity (58); at least one third internal cavity (62) extending axially between the upstream and downstream transverse walls (16a, 16b) of said ring segment (16) and circumferentially offset relative to said second cavity (60); at least one fourth internal cavity (64) extending axially between the upstream and downstream transverse walls (16a, 16b) of said ring segment (16) and circumferentially offset relative to said third cavity (62); at least first and second cooling air feed orifices (60, 68) leading from the cooling chamber (26) into said second and third cavities (60, 62) respectively in order to feed said second and third cavities; at least first and second passages (70, 72) putting respectively said second cavity (60) into communication with said first cavity (58), and said third cavity (62) 35 into communication with said fourth cavity (64); a plurality of first outlet holes (74) leading from said first cavity (58) into the hot gas passage (14) through the longitudinal wall (16c, 16d) of said ring segment (16) beside which said first internal cavity (58) is disposed; and a plurality of second outlet holes (76) leading from 5 said fourth cavity (64) into the hot gas passage (14) through the other longitudinal wall (16d, 16c) of said ring segment (16). 7. A ring (4) as claimed in claim 6, wherein each of said second and third internal cavities (60, 62) of the bottom cooling circuit (Bl) includes baffles (78) for increasing heat transfer. 8. A ring (4) as claimed in claim 6 or claim 7, wherein said first and second feed orifices (66, 68) of the bottom cooling circuit (B') are formed beside one of the transverse walls (16b, 16a) of said ring segment (16) and said first and second passages (70, 72) of the bottom cooling circuit (B') are formed beside the other transverse wall (16a, 16b) of said ring segment (16) so as to increase the cooling air flow path length.

Documents:

4851-DELNP-2005-Abstract-(27-07-2011).pdf

4851-delnp-2005-abstract.pdf

4851-DELNP-2005-Claims-(27-07-2011).pdf

4851-delnp-2005-claims.pdf

4851-DELNP-2005-Correspondence Others-(27-07-2011).pdf

4851-delnp-2005-correspondence-others.pdf

4851-delnp-2005-description (complete).pdf

4851-DELNP-2005-Drawings-(27-07-2011).pdf

4851-delnp-2005-drawings.pdf

4851-delnp-2005-form-1.pdf

4851-delnp-2005-form-2.pdf

4851-DELNP-2005-Form-3-(27-07-2011).pdf

4851-delnp-2005-form-3.pdf

4851-delnp-2005-form-5.pdf

4851-DELNP-2005-GPA-(27-07-2011).pdf

4851-delnp-2005-gpa.pdf

4851-delnp-2005-pct-210.pdf