JP2014511991A - Combustion chamber housing and gas turbine including the same - Google Patents

Abstract

  A combustion chamber housing (10) and a gas turbine (1) comprising the combustion chamber housing (10), the combustion chamber housing having a smoke tube (20) and a cladding tube (30), the cladding tube (30) Encloses the smoke pipe (20), and a plurality of through holes (31) are provided in the wall of the cladding pipe (30), and the air flowing toward the cladding pipe on the outside is provided in the through holes. Through (31), it can flow into the intermediate space (40) formed between the cladding tube and the smoke tube in the radial direction. According to the present invention, the distribution of air flowing around the smoke pipe becomes more uniform. In particular, the guide ribs (50) are distributed and arranged in the circumferential direction of the two tubes in the intermediate space, and these guide ribs (50) are arranged in the radial direction between the cladding tube and the smoke tube, respectively. This is achieved by extending parallel to the longitudinal direction (LR) of the tube and thereby dividing the intermediate space into a plurality of longitudinal tubes (41) by guide ribs.

Description

  The invention relates to a combustion chamber housing according to claim 1 and a gas turbine comprising such a combustion chamber housing.

  The combustion chamber housing and the gas turbine as described above are known from, for example, Patent Document 1. The combustion chamber housing described therein is a component of a combustion chamber of a gas turbine and has a smoke tube and a cladding tube or baffle screen, the cladding tube or baffle screen surrounding the smoke tube, The wall is provided with a plurality of through holes, and compressed air that flows toward the cladding tube on the outside passes through these through holes in a radial direction, in an intermediate space formed between the cladding tube and the smoke tube. Inflow.

  The combustion chamber is implemented as a single module, as a single combustor arranged in a ring, or as a ring combustion chamber. With the exception of the ring-shaped combustion chamber, these types always have a cylindrically configured smoke tube located inside.

  In the gas turbine as described above, the combustion air is first sucked in at atmospheric pressure and then compressed in the compressor of the gas generator. The compressor can be implemented radially or axially. In the combustion chamber that follows downstream from there, the combustion air is largely redirected to flow into the combustion zone. In other words, the combustion air is first supplied in a radial direction with respect to the combustion chamber into an intermediate space formed between the cladding tube and the smoke tube and then redirected so that an axial flow towards the combustor is achieved. Made.

  Within the intermediate space, there is a circumferential or rotating flow around the smoke tube, which is mostly cylindrical, thereby creating stagnation points and wakes with respect to the pressure distribution or flow distribution of the combustion air. In addition, in such a non-uniform mass flow distribution, this non-uniformity is maintained when the flow is greatly diverted as described above. Thereby, the cooling of the components located downstream becomes non-uniform, and the inside of the combustion zone becomes unstable because the air content changes.

German Patent No. 102006042124

  An object of the present invention is to provide a combustion chamber housing and a gas turbine having the same according to claim 1, wherein it is ensured that the distribution of air flowing around the smoke pipe is made more uniform.

  This is achieved by a combustion chamber housing according to claim 1 or a gas turbine according to claim 10. Developments of the invention are defined in the dependent claims.

  In a first aspect of the invention, there is provided a combustion chamber housing, particularly a combustion chamber housing for a gas turbine, which preferably has a cylindrical smoke tube, and preferably a cylindrical cladding tube or baffle screen. The cladding tube or baffle screen encloses and surrounds the smoke tube, and has a plurality of through holes in its wall, and compressed air (cooling air and combustion) flowing toward the cladding tube on the outside Air) can flow radially through the through-holes into a preferably cylindrical intermediate space formed between the cladding tube and the smoke tube. The combustion chamber housing of the present invention is characterized by a plurality of guide ribs that are distributed and arranged in the circumferential direction of both tubes (smoke tube and cladding tube) in the intermediate space, and these guide ribs are respectively a cladding tube and a smoke tube. The intermediate space is provided with a through-hole by a guide rib because it extends in the radial direction between and between and parallel to the longitudinal direction of the cladding tube and the smoke tube and along the longitudinal direction. The length of the coated tube is divided into a plurality of longitudinal tubes, preferably extending substantially over the entire length, preferably each having an annular sector cross section.

  The guide ribs are located in a direction transverse to the direction in which air flowing in during operation flows, and serve to interrupt or inhibit the flow around the smoke pipe. Thereby, the air flow is more evenly distributed and the cooling of the smoke tube is less disturbed. Furthermore, the cooling air and the combustion air are guided like a conduit after being redirected from a radial flow to an axial flow, so that the flow toward the subsequent combustion zone is homogeneous.

  By optimizing the air inflow, a homogeneous air / fuel mixture can be formed, particularly in the combustion chamber of a gas turbine with the combustion chamber housing of the present invention, thereby stabilizing the flame in the combustion process. Stay in the center of the combustion chamber. Any tilt or fluctuation of the flame will cause a local temperature rise in the surrounding components, which may cause excessive loading, but this is avoided by the guide ribs.

  As a result, the use of a combustion chamber housing constructed in accordance with the present invention in the combustion chamber of a gas turbine minimizes air supply non-uniformity, thus limiting the operation of the combustion chamber at the maximum design temperature. Can be done.

  In the present invention, the guide rib is desirably attached to the cladding tube. Each guide rib extends radially so that a gap is preferably formed between the guide rib and the smoke pipe.

  This gap is suitable to avoid distortions or stresses that can occur due to different material properties and thermal expansion properties. Since the flow is always directed radially outward and toward the side surface on which the flow guide ribs are also attached (inner circumference of the cladding tube), the cross flow generated through this gap is negligible.

  The guide ribs of the present invention are preferably each formed in a thin plate shape, each width extending in the radial direction of the cladding tube and the smoke tube, and each length extending in the axial direction or the longitudinal direction. The thickness of each guide rib is desirably about 3 mm.

  The guide rib and the through hole formed in the wall of the cladding tube of the present invention are desirably arranged so that the guide rib does not block any through hole. This preferably ensures that the radial flow of air to the intermediate space takes place optimally or unimpeded.

  According to a preferred embodiment of the present invention, the number of guide ribs provided in the intermediate space is exactly eight, and all the guide ribs have the same configuration.

  According to the present invention, the guide ribs are preferably arranged at different angular distances in the circumferential direction in the intermediate space. The angular distance is desirably in the range of approximately 28 degrees to approximately 126 degrees Celsius.

  In the present invention, preferably, the guide rib has a first guide rib group and a second guide rib group, and the first guide rib group is arranged in a given first arrangement pattern with respect to a circumferential angular distance of each other. The second guide rib groups are arranged in a second arrangement pattern with respect to each other in the circumferential angular distance, and this second arrangement pattern is a mirror image of the first arrangement pattern with respect to the axis of symmetry of the smoke tube. . Preferably, this axis of symmetry extends through the center of the smoke tube as viewed in cross section.

  According to a second aspect of the present invention, a gas turbine is provided with one, more or all of the preferred embodiments of the combustion chamber housing of the present invention described above in any combination.

  The invention also includes embodiments that do not rely on the combination of the features of the explicitly cited claims, and therefore the disclosed features of the invention can be arbitrarily combined with each other as long as they are technically meaningful. Can do.

1 is a perspective view of a combustion chamber housing of a combustion chamber of a gas turbine according to one embodiment of the present invention, a portion of which is shown in perspective. FIG. 2 is a front view of the combustion chamber housing of FIG. 1 without a smoke tube. FIG. 3 is a cross-sectional view of the combustion chamber housing of FIG. 1 as viewed along line AA in FIG. 2. . FIG. 3 is two cross-sectional views comparing the air flow and pressure distribution in the combustion chamber housing of FIG. 1 with and without guide ribs.

  Hereinafter, embodiments of the present invention will be described in detail with reference to preferred embodiments and drawings.

  A gas turbine 1 (not shown in its entirety) having a combustion chamber housing 10 according to an embodiment of the present invention will be described below with reference to FIGS.

  The combustion chamber housing 10 of the gas turbine 1 has a cylindrical smoke tube 20 and a cylindrical cladding tube or baffle screen 30, and the cylindrical cladding tube or baffle screen 30 encloses and surrounds the smoke tube 20. In addition, the wall of the cylindrical cladding tube or baffle screen 30 is provided with a plurality of through holes 31 that are evenly distributed around the circumference and flows toward the cladding tube 30 on the outer periphery. A cylindrical shape in which air (cooling air and combustion air) compressed by a compressor (not shown) of the turbine 1 is formed between the cladding tube 30 and the smoke tube 20 in the radial direction through the through holes 31. Can flow into the intermediate space 40.

  In the intermediate space 40, a plurality of (here, exactly eight) identical guide ribs 50 are provided which are distributed and arranged in the circumferential direction of the two tubes (the smoke tube 20 and the cladding tube 30). The guide ribs 50 extend in the radial direction between the cladding tube 30 and the smoke tube 20, parallel to the longitudinal direction LR of the cladding tube 30 and the smoke tube 20, and along the longitudinal direction LR. Accordingly, the intermediate space 40 is divided by the guide rib 50 into a plurality of longitudinal tubes 41 each having an annular fan-shaped cross section that extends substantially over the length of the cladding tube 30 provided with the through holes 31. The

  Due to the presence of the guide rib 50, it is reliably avoided that air flowing in the radial direction through the through-hole 31 during operation generates a component of the flow rotating in the circumferential direction or around the smoke pipe 20 in the intermediate space 40. Is done. Thereby, the air flow around the smoke tube 20 can be more evenly distributed, and the cooling of the smoke tube 20 is also improved. Furthermore, the air is diverted from radial to axial flow (by impinging on the smoke tube 20) and then guided in a longitudinal manner in the longitudinal tube 41 so that a subsequent combustion zone (not shown) ) Can be made uniform.

  The guide ribs 50 are attached (for example, welded) to the inner periphery of the cladding tube 30, and each guide rib 50 extends in the radial direction so that a gap S is formed between the guide rib 50 and the smoke tube 20. ing. The radial width of the gap S is such that, during operation of the gas turbine 1, various material expansions of the smoke tube 20, the cladding tube 30, and the guide rib 50 due to heat are not caused by the guide rib 50 being pressed against the smoke tube 20. The width is just enough to compensate.

  Each of the guide ribs 50 is formed in the shape of a metal piece. The width of each guide rib 50 extends in the radial direction of the cladding tube 30 and the smoke tube 20, and the length of each guide rib 50 extends in the axial direction or the longitudinal direction LR. Yes. At this time, the thickness of each guide rib 50 is about 3 mm.

  In particular, as can be seen from FIG. 3 (the left half of the figure), the guide rib 50 and the through hole 31 formed in the wall of the cladding tube 30 are arranged so that none of the through holes 31 are blocked by the guide rib 50. .

  As can be seen from FIGS. 1 and 2 in particular, the guide ribs 50 are arranged in the intermediate space 40 at different angular distances in the circumferential direction.

  The guide rib 50 includes a first group of guide ribs 50 (arranged to the left of the symmetry axis Y of the smoke tube 20 in FIG. 2) and a first group of the guide ribs 50 (arranged to the right of the symmetry axis Y in FIG. 2). There are two groups. According to the illustrated embodiment of the present invention, the first group of guide ribs 50 are arranged in a given first arrangement pattern with respect to each other's circumferential angular distance, and the second group of guide ribs 50 is arranged with respect to each other. Are arranged in a second arrangement pattern with respect to the circumferential direction angular distance, and this second arrangement pattern is a mirror image of the first arrangement pattern in the symmetry axis Y.

  According to the embodiment of the present invention illustrated in FIG. 2, the given first arrangement pattern of the first group of guide ribs 50 has angular dimensions a = 27 degrees, b = 1.8 degrees, c = 34.2 degrees, d = 59.4 degrees. The second arrangement pattern of the second group of guide ribs 50 is defined by angular dimensions a ′ = 27 degrees, b ′ = 1.8 degrees, c ′ = 34.2 degrees, and d ′ = 59.4 degrees.

  In other words, according to FIG. 2, in each group of the guide ribs 50, the angular distance between the guide ribs 50 is a combination of 28.2 degrees, 32.4 degrees, and 25.2 degrees, and the angular distances of both groups of the guide ribs 50 are 61. 2 degrees (lower part of FIG. 2) or 126 degrees (upper part of FIG. 2).

  According to another embodiment of the present invention not shown, the first and second arrangement patterns may be completely different. The respective angular distances of the first and second arrangement patterns or guide ribs 50 can be specially realized depending on the respective embodiment of the gas turbine 1, for example in terms of dimensions and / or shape, whereby It can be adapted to the special flow situation that occurs.

  FIG. 4 illustrates a comparison of air flow and pressure distribution in the combustion chamber housing 10 in two cross-sectional views. The combustion chamber housing in the upper diagram of FIG. 4 is not provided with the guide rib 50. 4 is provided with a guide rib 50 in the combustion chamber housing according to the present invention.

  As can be seen from the upper diagram of FIG. 4, when there is no guide rib 50, the flow of air and the pressure state in the intermediate space 40 are due to the circumferential flow of the smoke pipe 20 during operation of the gas turbine 1. It becomes non-uniform.

  As can be seen from the lower diagram of FIG. 4, during the operation of the gas turbine 1, the circumferential flow of the smoke tube 20 is obstructed by the guide ribs 50 that are located in a direction transverse to the direction in which the incoming air flows. As a result, the air flow and pressure conditions in the intermediate space 40 are substantially uniform, whereby the air flowing around the smoke tube 20 is evenly distributed and the cooling of the smoke tube 20 is improved. In addition, the air is redirected from a radial flow to an axial flow and then guided in a conduit, so that the flow toward the subsequent combustion zone is homogeneous.

DESCRIPTION OF SYMBOLS 1 Gas turbine 10 Combustion chamber housing 20 Smoke pipe 30 Cladding pipe 31 Through hole 40 Intermediate space 41 Longitudinal pipe 50 Guide rib S Gap LR Longitudinal direction Y Symmetry axis a, b, c, d Angular dimensions a ′, b ′, c ′, d 'Angular dimension

Claims (8)

A combustion chamber housing (10) of a gas turbine (1), comprising a smoke tube (20) and a cladding tube (30), the cladding tube (30) surrounding the smoke tube (20), The wall of the cladding tube (30) is provided with a plurality of through holes (31), and air flowing toward the cladding tube (30) on the outside passes through the plurality of through holes (31). In the combustion chamber housing (10) that can flow radially into the intermediate space (40) formed between the cladding tube (30) and the smoke tube (20),
A plurality of flow guide ribs (50) are distributed and arranged in the circumferential direction of the two pipes in the intermediate space (40), and the plurality of flow guide ribs (50) are respectively connected to the cladding pipe (30) and The plurality of flow guide ribs (50) extend radially between the smoke pipe (20) and parallel to the longitudinal direction (LR) of the cladding pipe (30) and the smoke pipe (20). Is fixed only to the cladding tube (30), and a gap (S) is formed with respect to the smoke tube (20) at least when the gas turbine (1) is at rest, whereby the intermediate space (40) is formed. ) Is divided into a plurality of longitudinal tubes (41) by the flow guide rib (50).   The combustion chamber housing (10) according to claim 1, characterized in that the flow guide ribs (50) are each formed in a thin plate shape.   Combustion chamber housing (10) according to claim 2, characterized in that the flow guide rib (50) has a thickness of 3 mm.   The flow guide rib (50) and the through hole (31) formed in the wall of the cladding tube (30) are prevented from being blocked by the flow guide rib (50). Combustion chamber housing (10) according to any one of claims 1 to 3, characterized in that it is arranged in   The combustion chamber housing (1) according to any one of claims 1 to 4, characterized in that the plurality of flow guide ribs (50) are formed from exactly eight identical flow guide ribs (50). 10).   Combustion according to any one of the preceding claims, characterized in that the flow guide ribs (50) are arranged in the intermediate space (40) at different angular distances in the circumferential direction. Chamber housing (10).   The flow guide rib (50) has a first group of flow guide ribs (50) and a second group of flow guide ribs (50), the first group of flow guide ribs (50) being their respective circles. Arranged in a given first arrangement pattern with respect to the circumferential angular distance, and the second group of flow guide ribs (50) is arranged in a second arrangement pattern with respect to their circumferential angular distance. The second arrangement pattern is a mirror image of the first arrangement pattern in the axis of symmetry (Y) of the smoke pipe (20). A combustion chamber housing (10) according to claim 1.   A gas turbine (1) comprising a combustion chamber housing (10) according to any one of the preceding claims.