JP4690353B2 - Gas turbine sealing device - Google Patents

Gas turbine sealing device Download PDF

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JP4690353B2
JP4690353B2 JP2007059850A JP2007059850A JP4690353B2 JP 4690353 B2 JP4690353 B2 JP 4690353B2 JP 2007059850 A JP2007059850 A JP 2007059850A JP 2007059850 A JP2007059850 A JP 2007059850A JP 4690353 B2 JP4690353 B2 JP 4690353B2
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flow path
cooling
gas turbine
working fluid
side
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JP2008223515A (en
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康広 堀内
雅美 野田
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株式会社日立製作所
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Description

  The present invention relates to a gas turbine seal device that suppresses leakage of a working fluid.

  In the gas turbine, outside the gas flow path through which the high-temperature combustion gas (working fluid) obtained by burning with fuel in the combustor flows, the compressor is installed so that the components of the gas flow path are not damaged by heat. The extracted cooling air is supplied. Further, the constituent members of the gas flow path are divided into a plurality of parts in consideration of thermal deformation, maintainability, etc., as in the other parts. Therefore, for example, the air supplied to the outside of the gas flow path is maintained at a high pressure compared to the pressure of the combustion gas so that the combustion gas does not leak outside through the gap between the members. However, in this state, the cooling air leaks from the gap into the gas flow path, and the temperature of the working gas decreases, which may cause a decrease in the thermal efficiency of the gas turbine. Therefore, the structural members are connected to each other via a sealing device provided in the gap, and the excessive leakage of the cooling air to the working gas side is suppressed.

  By the way, in a gas turbine for power generation, there is a great expectation for improvement in performance and efficiency including a combined cycle combined with a steam turbine, and further higher temperature of the working fluid is particularly demanded. . For this reason, there is a need to actively cool the connecting portions of the constituent members that are less required to be cooled in other gas turbines, and the sealing device used for the connecting portions has high cooling efficiency and reliable. What has a sealing performance is calculated | required.

  As this type of technology, there is a technique in which a plurality of holes (slots) are provided in a seal plate that connects gas flow path component members, and the film in the vicinity of the connecting portion is cooled by air passing through the holes (patent) Reference 1 etc.).

US Pat. No. 4,767,260

  However, in the above technique, since the cooling air can exchange heat with the high temperature member only when passing through the hole of the seal plate, it is released into the working fluid with little use of its own cooling potential. In addition, if the heat exchange of the cooling air is insufficient and the heat is released into the working fluid while the temperature is low, the temperature of the working fluid is lowered drastically, and the efficiency of the entire gas turbine is lowered. Furthermore, the cooling air passing through the holes may disturb the flow of the working fluid, which may cause further reduction in efficiency.

  An object of the present invention is to provide a sealing device having excellent cooling efficiency and sealing performance.

  (1) In order to achieve the above object, the present invention is a pair of flow paths that are arranged such that their side portions face each other with a gap therebetween, and define a working fluid flow path and a cooling fluid flow path. A pair of grooves provided on each side of the pair of flow path component members so as to face each other with the gap between them, and of the two sets of grooves, on the flow path side of the working fluid A plate that spans the groove, and another plate that has a plurality of cooling holes that are spanned by the channel on the flow path side of the cooling fluid among the two sets of grooves and that are provided at the position of the gap. And

  (2) In order to achieve the above object, the present invention defines a working fluid flow path and a cooling fluid flow path, and the working fluid flow path side portion is more than the cooling fluid flow path side portion. Contrary to the shape of the side portion of the flow path component, the flow path component on the cooling fluid side protrudes from the flow path side portion of the working fluid, opposite to the shape of the side of the flow path component. A side portion having a shape, the side portion being disposed so as to face the side portion of the flow path component member with a gap therebetween, and together with the flow path component member, the flow path of the working fluid and the cooling fluid The other flow path constituting member that defines the flow path, the protruding portion of the side portion of the flow path constituting member, and the side portion of the other flow path constituting member that faces the same are opposed to each other through the gap. And a pair of grooves provided on the side of the other flow path component Another set of grooves provided to face each other through the gap on the side portion of the flow path component member facing the portion, and a plate spanned across the set of grooves, And another plate having a plurality of first cooling holes provided in the gap and spanning the other set of grooves.

  (3) In the above (2), preferably, the flow path component member has a surface on which the cooling fluid ejected from the plurality of first cooling holes of the other plate directly collides toward the flow path side of the working fluid. It shall have the recessed part provided backward.

  (4) In the above (2), preferably, the flow path component member faces the flow path of the working fluid from an inlet provided in a portion sandwiched between the two plates on the side portion. It shall be provided with a plurality of 2nd cooling holes provided so that it may penetrate diagonally to the provided spout.

  (5) In the above (4), preferably, the plurality of second cooling holes are provided at the outlets of the gaps.

  (6) In the above (4), preferably, the inflow ports of the plurality of second cooling holes are provided at positions deviating from the axial centers of the plurality of first cooling holes.

  (7) In the above (4), preferably, the second cooling hole is provided so as to be inclined such that the direction thereof follows the flow direction of the working fluid in the flow path of the working fluid. .

  (8) In the above (2), preferably, the flow path component is formed from the inflow port provided at a portion sandwiched between the two plates on the side portion, and the working fluid from the plate in the gap. A plurality of third cooling holes provided so as to penetrate to a jet port provided in a portion located on the flow path side of the above.

  According to the present invention, since excellent cooling efficiency and sealing performance can be exhibited, the efficiency and reliability of the gas turbine can be improved.

  Hereinafter, embodiments of the present invention will be described with reference to the drawings.

  FIG. 1 is a cross-sectional view of a gas turbine seal device according to a first embodiment of the present invention, and FIG. 2 is a perspective view thereof.

  The gas turbine sealing device shown in these drawings is arranged such that the side portions 11 and 12 face each other with a gap 10 therebetween, and the working fluid flow path (working fluid flow path) 4 and the cooling fluid of the gas turbine are arranged. A pair of flow path component members 1 and 2 that define the flow path (cooling fluid flow path) 3, and the side portion 11 of the flow path component member 1 and the flow path component member 2 so as to face each other with a gap 10 therebetween. Two sets of grooves 51, 52 and 61, 62 respectively provided in the side portion 12, a seal plate 6 spanning the grooves 61, 62 on the working fluid flow path 4 side, and the cooling fluid flow path 3 side An impingement plate 5 that spans the grooves 51 and 52 and has a plurality of impingement cooling holes 53 is provided.

  The working fluid channel 4 is a channel (gas path) through which high-temperature combustion gas (working fluid) obtained by mixing compressed air compressed by a compressor (not shown) and fuel in a combustor (not shown) flows. ). Although details will be described later, as an example of this flow path 4 in the gas turbine, a flow path (hereinafter, referred to as a plurality of stationary blades) is formed in an annular shape on the outer periphery of a turbine rotor (not shown). An annular channel).

  Since the member forming the working fluid flow path 4 is exposed to a high temperature by the working fluid, a plurality of members are provided from the viewpoint of alleviating stress concentration due to thermal deformation and facilitating inspection, maintenance, and replacement of parts. There is something divided. The members divided into a plurality of parts correspond to the above-described flow path constituting members 1 and 2 and constitute the working fluid flow path 4 adjacent to each other.

  The flow path component members 1 and 2 form a working fluid flow path 4 together with other flow path component members (not shown), and are arranged so that the side portions 11 and 12 are adjacent to each other. For example, when the flow path component members 1 and 2 constitute a part of an annular flow path formed on the outer periphery of the turbine rotor, a segment that forms a plurality of annular flow paths in the circumferential direction of the turbine rotor. Of the surfaces constituting the members, the surfaces facing the working fluid flow path 4 constitute end walls.

  The cooling fluid channel 3 is a channel for circulating a relatively low temperature fluid (cooling fluid) compared to the working fluid, and is formed so as to cover the working fluid channel 4 from the outside or the inside. . The cooling fluid suppresses the flow path components 1 and 2 from being dissolved by being exposed to the working fluid, or being cracked and damaged by oxidation or thermal stress. By the way, since the gap 10 exists between the flow path components 1 and 2 as described above, the high-temperature working fluid may leak out of the working fluid flow path 4 through the gap 10. Therefore, it is necessary to supply a fluid having a relatively high pressure as the cooling fluid as compared with the working fluid. In the cooling fluid channel 3 in the present embodiment, compressed air extracted from the compressor flows to suppress leakage of the working fluid.

  The side portion 11 of the flow path component 1 and the side portion 12 of the flow path component 2 are portions where the flow path component 1 and the flow path component 2 are connected by the plates 5 and 6 while holding a predetermined gap 10. It is. A groove 51 and a groove 61 are provided in the side portion 11 of the flow path component 1, and a groove 52 and a groove 62 are provided in the side portion 12 of the flow path component 2.

  The groove 51 and the groove 52, the groove 61 and the groove 62 are two sets of grooves arranged so as to face each other with the gap 10 therebetween, and the two sets of grooves 51, 52 and 61, 62 are the cooling fluid channel 3. To the working fluid flow path 4 (or the opposite direction, that is, the turbine rotor radial direction). The impingement plate 5 is inserted into the grooves 51 and 52, and the seal plate 6 is inserted into the grooves 61 and 62 as indicated by the arrows in FIG.

  Between the impingement plate 5 and the grooves 51 and 52 and between the seal plate 6 and the grooves 61 and 62 are not completely sealed, and minute gaps (seal gaps 71 and 72) are formed. Therefore, the flow of the cooling fluid generated by the pressure difference between the working fluid and the cooling fluid becomes a discharge flow 32 through the seal gaps 71 and 72 formed around the seal plate 6 and is released to the working fluid flow path 4 side. ing. Here, the seal gap 71 is a gap formed between the seal plate 6 and the groove 61, and the seal gap 72 is a gap formed between the seal plate 6 and the groove 62.

  Since the discharge flow 32 may disturb the flow of the working fluid in the working fluid channel 4 and reduce the efficiency when an excessive amount flows into the working fluid channel 4, the working fluid is cooled by the cooling fluid channel 3. The flow rate is adjusted so that there is no back flow. Further, in a general gas turbine that uses air extracted from a compressor as a cooling fluid, if the amount of extraction is increased unnecessarily, the amount of working fluid may decrease and the efficiency of the entire gas turbine may decrease. Therefore, the flow rate of the discharge flow 32 is also adjusted from this viewpoint.

  In order to adjust the flow rate of the discharge flow 32 as described above, the number and diameter of the impingement cooling holes 53 may be changed and the flow rate of the cooling fluid reaching between the impingement plate 5 and the seal plate 6 may be adjusted. Thereby, the trouble of adjusting the size of the seal gaps 71 and 72 formed between the seal plate 6 and the grooves 61 and 62 by changing the surface roughness of the plate 6 and the grooves 61 and 62 is reduced. Thus, the flow rate of the discharge flow 32 can be easily adjusted.

  The impingement cooling hole 53 provided in the impingement plate 5 has an ejection port 53a provided on the working fluid flow path 4 side so as to face the seal plate 6. With such a configuration, the cooling fluid (compressed air) flowing into the cooling hole 53 from the cooling fluid flow path 3 due to a pressure difference is blown toward the seal plate 6 and collides with the jet 31 to jet the seal plate 6. Cool (impinge cooling).

  In the gas turbine sealing apparatus configured as described above, a part of the cooling fluid in the cooling fluid flow path 3 enters the gap 10 and becomes a jet 31 through the impingement cooling hole 53 to collide with the seal plate 6. To do. In this collision, the cooling fluid exchanges heat with the seal plate 6 and uses its cooling potential, so that the cooling fluid can be efficiently cooled as compared with the case of simply passing through the vicinity of the seal plate 6 and cooling. A part of the cooling fluid colliding with the seal plate 6 is adjusted to an amount suitable for preventing the backflow of the working fluid when passing through the seal gaps 71 and 72 formed between the seal plate 6 and the grooves 61 and 62. A discharge flow 32 is discharged into the working fluid flow path 4.

Next, the effect of this embodiment will be described.
First, a comparative example of this embodiment will be described in order to facilitate understanding of the effects of this embodiment.

  FIG. 3 is a perspective view of a sealing device for a gas turbine which is a first comparative example of the first embodiment of the present invention. The gas turbine sealing device shown in this figure includes a pair of flow path component members 101 and 102, a pair of grooves 161 and 162 provided on the side of the flow path component members 101 and 102, and grooves 161 and 162. It is provided with a seal plate 206 spanned between the two and is generally used as a sealing device for a connecting portion.

  FIG. 4 is a top view of a gas turbine seal device as a second comparative example of the first embodiment of the present invention, and FIG. 5 is a perspective view thereof. In addition, the same code | symbol is attached | subjected to the same part as the previous figure, and description of the part is abbreviate | omitted (it is the same also in later figures). The gas turbine seal device shown in FIGS. 4 and 5 is provided with a plurality of slits 163 through which a cooling fluid flows, and is provided with a seal plate 106 laid across grooves 161 and 162, which is a first comparative example. The sealing device is improved from the viewpoint of cooling performance. This sealing device cools the film in the vicinity of the connecting portion by the cooling fluid that passes through the slit 163.

  However, since the cooling fluid in the second comparative example can exchange heat with the seal plate 106 only while passing through the slit 163, the cooling efficiency is poor. Further, since the cooling fluid cannot sufficiently use the cooling potential possessed by the cooling fluid, the cooling fluid may be discharged into the working fluid at a relatively low temperature, and the temperature of the working fluid may be lowered excessively. Furthermore, since a large amount of cooling fluid can easily flow into the working fluid flow path through the slit 163, the flow of the working fluid may be disturbed, both of which are factors in reducing the efficiency of the entire gas turbine. End up.

  On the other hand, the gas turbine seal device of the present embodiment includes a seal plate 6 spanning the grooves 61 and 62 on the working fluid flow path 4 side and grooves 51 and 52 on the cooling fluid flow path 3 side. An impingement plate 5 is provided which has a plurality of impingement cooling holes 53. According to the sealing device configured as described above, the cooling potential of the cooling fluid can be sufficiently used by jet cooling the seal plate 6 using the jet 31 ejected from the impingement cooling hole 53. Therefore, the flow path component members 1 and 2 can be efficiently cooled, and the cooling fluid having a high cooling potential is not released into the working fluid and the temperature of the working fluid is not lowered drastically as in the comparative example. . Further, since the cooling fluid used for cooling the seal plate 6 is sealed by the seal plate 6, the discharge amount to the working fluid can be suppressed as much as possible, so that the loss generated when the cooling fluid is mixed with the working fluid. (Mixing loss) can be reduced.

  6 shows the cooling effect of the first comparative example having the structure shown in FIG. 3, the second comparative example having the structure shown in FIGS. 4 and 5, and the sealing device of each embodiment according to the present invention. It is a comparison. When comparing each sealing device, the pressure difference of each fluid is 0.2 [MPa], the temperature of the cooling fluid is 300 [° C.], the seal gap is 0.2 [mm], the impingement cooling hole 53 and the slit The diameter of 163 etc. was 1 [mm], and the hole interval was 10 [mm].

  In this figure, “the flow rate of the cooling fluid that passes” indicates the flow rate of the cooling fluid that flows into the working fluid flow path 4 via the seal device, and represents the flow rate in other cases with the flow rate of the first comparative example as a reference. ing. The “heat transfer coefficient of the seal gap” indicates the heat transfer coefficient when the cooling fluid flows through the seal gaps 71 and 72, and the “heat transfer coefficient of the jet collision surface” indicates the jet 31 from the impingement cooling hole 53. The “heat transfer coefficient of forced convection cooling” indicates the heat transfer coefficient by the forced convection cooling flow 34 from the cooling hole 9D and the cooling hole 13 in the fifth and sixth embodiments described later. .

  As shown in this figure, in the first comparative example, the heat transfer coefficient of the seal gap is only 937 [W / m 2 / ° C.], whereas in the second comparative example in which the slit 163 is added, the heat transfer coefficient of the seal gap is only compared to the first comparative example. Thus, 4.8 times as much cooling fluid is released into the working fluid. On the other hand, the sealing device of the present embodiment has a cooling fluid passage flow rate substantially equal to that of the first comparative example, and has a heat transfer coefficient 929 [W / m 2 / ° C.] of the seal gap substantially equal to that of the first comparative example. The thermoelectric conductivity of the jet collision part can be set to 941 [W / m 2 / ° C.].

  Thus, according to the present embodiment, excellent cooling efficiency and sealing performance can be exhibited at the same time, so that the efficiency and reliability of the gas turbine can be improved. In addition, this makes it possible to use an inexpensive material having a low heat-resistant temperature as a material for the member such as the seal plate 6 used for the connecting portion of the flow path component member, so that the manufacturing cost of the gas turbine can be reduced.

  Further, according to the present embodiment, the flow rate adjustment of the discharge flow 32 discharged from the gap 10 through the seal gaps 71 and 72 formed between the seal plate 6 and the grooves 61 and 62 is performed by the impingement cooling hole 53. This can be easily performed by adjusting the flow rate of the cooling fluid that collides with the seal plate 6 by changing the number and the diameter of the cooling fluid. Therefore, by precisely machining the surfaces of the seal plate 6 and the grooves 61 and 62, the trouble of adjusting the flow rate of the discharge flow 32 by adjusting the dimensions of the seal gaps 71 and 72 is reduced. You can also

  Next, a second embodiment of the present invention will be described.

  FIG. 7 is a sectional view of a gas turbine seal device according to a second embodiment of the present invention, and FIG. 8 is a perspective view thereof. A feature of this embodiment is that a bent flow path for cooling fluid is formed in a gap formed between the impingement plate 5 and the seal plate 6.

  The gas turbine sealing device shown in these drawings includes a flow path component 1A having a side portion 11 provided with a protruding portion 21, and a side portion 12 provided with a protruding portion 22, and the side portion 12 is A flow path component 2A is provided so as to face the side portion 11 of the flow path component 1A with a gap 10 therebetween.

  The protruding portion 21 is a portion provided such that a portion of the side portion 11 on the working fluid flow path 4 side protrudes from a portion on the cooling fluid flow path 3 side, and the protruding portion 22 is the shape of the side portion 11. On the contrary, it is a part provided so that the part by the side of the cooling fluid flow path 3 of the side part 12 may protrude from the part by the side of the working fluid flow path 4. A pair of grooves 61 and 62 are provided on the protruding portion 21 and the side portion 12 of the flow path component 2 </ b> A facing the protruding portion 21 so as to face each other with the gap 10 therebetween. In addition, a pair of grooves 51 and 52 are provided on the protruding portion 22 and the side portion 11 of the flow path component 1 </ b> A facing the protruding portion 22 so as to face each other with the gap 10 therebetween. The seal plate 6 is bridged over the grooves 61 and 62, and the impingement plate 5 is bridged over the grooves 51 and 52. Note that, from the viewpoint of ease of processing during manufacturing, the protruding portion 21 and the protruding portion 22 are preferably provided in a step shape as shown in FIG.

  The flow path component 1A defines the working fluid flow path 4 and the cooling fluid flow path 3 together with the flow path structure member 2A arranged adjacent to each other. The flow path component 1A and the flow path structure member 2A are arranged so that the protrusions 21 and 22 overlap each other, and form a flow path bent in a gap 10 formed therebetween.

  The gap 10 constituting the bent flow path includes a first bent portion 15, a second bent portion 16, and an intermediate flow path 17.

  The first bent portion 15 is a flow channel that is located immediately after passing through the impingement plate 5 from the cooling fluid passage 3 side, and has a shape that is greatly bent in accordance with the protruding shape of the protruding portion 21. The second bent portion 16 is a flow channel that is located downstream of the first bent portion 15 and immediately before the seal plate 6, and increases again toward the working medium flow channel 4 in accordance with the shape in the vicinity of the tip portion of the protruding portion 21. It consists of a bent shape. The intermediate flow path 17 is a flow path located between the first bent portion 15 and the second bent portion 16, and is constituted by the side portions 11 and 12 of the flow path constituting members 1A and 2A.

  In the gas turbine sealing apparatus configured as described above, a part of the cooling fluid in the cooling fluid flow path 3 enters the gap 10 and then becomes the jet 31 through the impingement cooling hole 53, and the first bent portion 15. At the side of the flow path component 1A. Thereby, the jet 31 cools the flow path component 1 </ b> A via the side portion 11.

  The cooling fluid that has cooled the flow path component 1A then flows through the intermediate flow path 17, and at this time, the second bent portion 16 is cooled while cooling the flow path components 1A and 2A via the side portions 11 and 12. Led to. The cooling fluid guided to the second bent portion 16 passes through the second bent portion 16 and is then guided to seal gaps 71 and 72 formed between the seal plate 6 and the grooves 61 and 62. When passing through the seal gaps 71, 72, the cooling fluid cools the seal plate 6 and is discharged into the working fluid flow path 4 as a discharge flow 32 in an amount suitable for preventing the backflow of the working fluid.

  According to the present embodiment, as shown in the table of FIG. 6, it is possible to obtain the cooling fluid passage flow rate and the heat transfer coefficient of the jet collision surface equivalent to those of the first embodiment. However, in the present embodiment, as described above, the flow path component 1A that is in direct contact with the working fluid can be directly cooled by the jet 31. Therefore, the cooling efficiency by the cooling fluid is improved by the first embodiment. It can be improved further. In particular, when the flow of the working fluid flows in the direction from the flow path component 1A to the flow path component 2A, the edge portion of the component member 1A has a high thermal load. It is preferable to have the above structure in which 21 is arranged on the working fluid flow path 4 side. Moreover, since the cooling fluid can cool the flow path component members 1A and 2A while passing through the intermediate flow path 17, the cooling efficiency is further improved.

  As described above, according to the present embodiment, the cooling efficiency superior to that of the first embodiment can be exhibited, so that the efficiency and reliability of the gas turbine can be further improved. .

  Here, the case where the sealing apparatus of this Embodiment is applied to a gas turbine is demonstrated.

  FIG. 9 is a partial cross-sectional view of a gas turbine to which the present embodiment is applied, and FIG. 10 is a partial cross-sectional view of the first stage stationary blade 111 on the plane AA in FIG.

  The gas turbine shown in FIG. 9 includes a first stage stationary blade 111, a first stage moving blade 112, a second stage stationary blade 113, a shroud 114, a casing 115, and a transition piece 116. An outer peripheral end wall 117 is provided on the outer side in the turbine rotor radial direction of the first stage stationary blade 111, and an inner peripheral side end wall 118 is provided on the inner side in the turbine rotor radial direction of the first stage stationary blade 111. An arrow 120 in FIG. 3 indicates the flow of the working fluid in the working fluid channel (corresponding to the working fluid channel 4 described above). Moreover, the part which the code | symbol 121,122,123,124 shows in a figure becomes the cooling fluid flow path (equivalent to said cooling fluid flow path 3) through which compressor discharge air distribute | circulates.

  As an application location of the sealing device of the present embodiment in such a gas turbine, first, there is a portion where flow path component members are connected along the turbine rotor axial direction. As a specific example, as shown in FIG. 9, the connection part of the transition piece 116 and the outer peripheral side end wall 117 of the first stage stationary blade 111, or the inner peripheral side end wall of the transition piece 116 and the first stage stationary blade 111. There are 118 connections. The flow path component is connected by the impingement plate 5 and the seal plate 6 at such a connecting portion.

  Moreover, as another application location, there exists a part by which the flow-path structural member is connected along the turbine rotor circumferential direction. As a specific example, as shown in FIG. 10, there is a connecting portion of a first stage stationary blade segment (hereinafter referred to as a segment) 130 which is a structural unit of the first stage stationary blade 111.

  In FIG. 10, a plurality of segments 130 are members that form an annular flow path by being connected together along the circumferential direction of the turbine rotor, and are fixed to the casing 115 in an annular shape. The segment 130 has an edge portion 131 and an impingement plate 119.

  The edge portion 131 has a protruding portion 132 where it becomes a connecting portion with another adjacent segment 130. The edge portion 131 is provided with a groove that spans the impingement plate 5 and the seal plate 6, and the adjacent segments 130 are connected to each other by the impingement plate 5 and the seal plate 6. The protruding portion 132 is a portion provided on the cooling fluid channel side of the edge portion 131 and protrudes toward the cooling fluid channel side.

  The impingement plate 119 is a member that is bridged around the protruding portion 132 of the edge portion 131 in the same segment 130 and fixed by welding or the like, and is provided with a plurality of through holes (not shown). The impingement plate 119 is disposed at a distance from the end walls 117 and 118 by an amount corresponding to the protruding portion 132 of the edge portion 131. The impingement plate 119 jets and cools the end walls 117 and 118 by the cooling fluid passing through the through holes. Yes.

  The segment 130 shown in FIG. 10 has two blades per segment (double blades), but the sealing device of the present embodiment is also applicable to a segment having a different number of blades. can do. Of course, the present invention can also be applied to the second stage stationary blade 113, the connecting portion of the shroud 114 segment, and the like.

  As described above, if the sealing device of the present embodiment is applied to the connection portion of the flow path component of the gas turbine, the connection portion of the flow path component that has been difficult to cool can be jet-cooled. At the same time, the discharge amount of the cooling fluid to the working fluid can be minimized.

  In addition, what can be applied to the location of the gas turbine as described above is not limited to the sealing device of the second embodiment. That is, it goes without saying that the sealing device of the first embodiment and the sealing device of each of the following embodiments are also applicable.

  Next, a third embodiment of the present invention will be described.

  FIG. 11 is a cross-sectional view of a gas turbine seal device according to a third embodiment of the present invention, and FIG. 12 is a perspective view thereof. The feature of this embodiment is that a recess (described later) is provided on the surface of the flow path constituting member 1A of the second embodiment on which the jet 31 collides.

  The flow path component 1B in the gas turbine seal device shown in these drawings is such that the surface of the impingement plate 5 on which the jet 31 ejected from the impingement cooling hole 53 directly collides is retracted toward the working fluid flow path 4 side. A provided recess (cooling cavity) 8 is provided. Other parts are the same as those of the second embodiment.

  The surface retreated to the working fluid flow path 4 side to form the recess 8 is disposed so as to face the ejection port of the impingement cooling hole 53 so that the jet 31 from the impingement cooling hole 53 directly collides with it. It has become.

  The thickness of the member from the recess 8 to the working fluid flow path 4 is preferably as thin as possible as long as the strength of the member allows, taking into account the plate 6 holding function of the grooves 61 and 62 and the like. This is because, in general, when cooling from the inside in order to keep the surface of the object to be cooled at a constant temperature, the thinner the object to be cooled, the better the cooling efficiency. Therefore, when the concave portion 8 is made as thin as possible in this way, the portion close to the contact surface with the working medium can be directly cooled, so that the flow path component 1B can be more effectively cooled.

  Also according to the present embodiment configured as described above, as shown in the table of FIG. 6, it is possible to obtain the cooling fluid passage flow rate and the heat transfer coefficient of the jet collision surface equivalent to those of the first embodiment. However, in the present embodiment, as described above, the jet 31 from the impingement cooling hole 53 can be injected to a portion closer to the working fluid flow path 4 compared to the case of the second embodiment. Compared with the second embodiment, the flow path component 1B can be more effectively cooled.

  As described above, according to the present embodiment, the cooling efficiency superior to that of the second embodiment can be exhibited, so that the efficiency and reliability of the gas turbine can be further improved.

  Next, a fourth embodiment of the present invention will be described.

  FIG. 13 is a sectional view of a gas turbine seal device according to a fourth embodiment of the present invention, and FIG. 14 is a perspective view thereof. The feature of this embodiment is that a film cooling hole connected to the working fluid flow path 4 is provided in the recess 8 of the flow path constituting member 1B of the third embodiment.

  In the gas turbine sealing device shown in these drawings, the flow path component 1 </ b> C includes a plurality of film cooling holes 9. The film cooling hole 9 has an inlet 91 provided in a portion of the gap 10 sandwiched between the impingement plate 5 and the seal plate 6, and an outlet 92 provided facing the working fluid flow path 4. Yes. Inflow port 91 in the present embodiment is provided in a part of recess 8. Other parts are the same as those of the third embodiment.

  The film cooling hole 9 is a hole that obliquely penetrates the working fluid flow path 4 from the inlet 91 to the jet outlet 92, and the cooling fluid that has flowed into the gap 10 is used as the film cooling flow 33 of the flow path component 1C. Spouts on the surface. The film cooling flow 33 ejected in this way covers the surface of the flow path component 1C and suppresses the temperature rise of the flow path component 1C (film cooling).

  The direction of the film cooling hole 9 (that is, the direction in which the ejection port 92 is provided with respect to the inflow port 91) is the flow direction of the working fluid in the working fluid flow path 4 (more precisely, the ejection port 92. It is preferable to provide it with an inclination so as to follow the traveling direction of the working fluid in FIG. In this way, since the film cooling flow 33 can be ejected along the flow direction of the working fluid, loss (mixing loss) that occurs when the cooling fluid is mixed with the working fluid can be reduced. In addition, the inlet 91 is preferably provided at a position off the axis of the impingement cooling hole 53. By providing in this way, the jet 31 can be prevented from flowing into the film cooling hole 9 without colliding with the side portion 11, so that the cooling efficiency by jet cooling can be maintained.

  According to the present embodiment configured as described above, the flow path component 1C can be film-cooled, so that the thermal load on the flow path component 1C can be reduced as compared with the third embodiment. it can. Therefore, the efficiency and reliability of the gas turbine can be further improved.

  Further, as shown in the table of FIG. 6, in the present embodiment, 3.2 times as much cooling fluid is discharged into the working fluid as compared to the first comparative example, but cooling that passes through the impingement cooling holes 53. By increasing the flow rate of the fluid, the heat transfer coefficient of the jet collision surface can be significantly improved to 2366 [W / m 2 / ° C.]. Further, the flow rate of the cooling fluid can be suppressed to a small flow rate as compared with the second comparative example.

  In the description of the present embodiment, the case where the film cooling hole 9 is provided in the third embodiment has been described as an example. However, the present invention is not limited to this, and for example, the seal of the second embodiment. Of course, it can also be applied to the apparatus.

  Next, a fifth embodiment of the present invention will be described.

  FIG. 15 is a cross-sectional view of a gas turbine seal device according to a fifth embodiment of the present invention, and FIG. 16 is a perspective view thereof. The feature of the present embodiment is that the jet outlet 92 of the film cooling hole 9 in the fourth embodiment is provided at the outlet of the gap 10 and is a modification of the fourth embodiment. .

  In the gas turbine sealing device shown in these drawings, the flow path component 1D is provided with a cooling hole 9D having a jet 92D provided at the outlet of the gap 10. Other parts are the same as those of the fourth embodiment.

  The ejection port 92 </ b> D is provided at an outlet portion where the cooling fluid flowing through the gap 10 is discharged to the working fluid flow path 4, and configures a cooling hole 9 </ b> D that is an oblique through hole together with the inflow port 91. Further, since the jet outlet 92D is provided on the gap 10 side as compared with the jet outlet 92 of the fourth embodiment, the length of the cooling hole 9D is longer than that of the film cooling hole 9 of the fourth embodiment. ing.

  In the present embodiment configured as described above, the cooling fluid that has flowed through the cooling hole 9 </ b> D becomes a forced convection cooling flow 34, and is ejected from the discharge flow 32 at the outlet of the gap 10. The discharge direction is changed toward the flow path component 2A. Since the discharge flow 32 whose discharge direction is changed in this way covers the surface of the flow path component 2A and acts as a film cooling flow, the temperature rise of the flow path component 2A is suppressed. Further, since the cooling hole 9D is a relatively long through-hole that passes through a portion close to the working fluid flow path 4 in the flow path constituting member 1D, the flow path constituting member 1D is more effective than the case of the fourth embodiment. Can be cooled to.

  As shown in the table of FIG. 6, according to the present embodiment, the heat transfer coefficient of the jet collision surface equivalent to that of the fourth embodiment can be obtained, and the forced convection cooling flow passing through the cooling hole 9D. 34, a heat transfer coefficient of 6343 [W / m 2 / ° C.] can be obtained.

  As described above, according to the present embodiment, since the flow path component 2A can be film-cooled, the thermal load on the flow path component 2A can be reduced, and the flow of fluid can be reduced by the cooling fluid passing through the cooling holes 9D. It is possible to reduce the thermal load on the path constituent member 1A. Therefore, the efficiency and reliability of the gas turbine can be improved as compared with the third embodiment.

  In addition, since the cooling hole 9D ejects the forced convection cooling flow 34 along the flow direction of the working fluid, the flow of the working fluid in the working fluid flow path 4 is the same as the film cooling hole 9 of the fourth embodiment. It is good to provide it so as to follow the direction. In addition, the inlet 91 is preferably provided at a position off the axis of the impingement cooling hole 53.

  In the description of the present embodiment, the case where the cooling hole 9D is provided in the third embodiment has been described as an example. However, the present invention is not limited to this, and for example, the sealing device of the second embodiment is also provided. Of course, it can be applied.

  Next, a sixth embodiment of the present invention will be described.

  FIG. 17 is a sectional view of a gas turbine seal device according to a sixth embodiment of the present invention, and FIG. 18 is a perspective view thereof. The feature of this embodiment is that an impingement cooling hole connected to the gap 10 is provided in the recess 8 of the flow path component 1B of the third embodiment.

  The flow path component 1E in the gas turbine seal device shown in these drawings includes a plurality of cooling holes 13 penetrating from the inflow hole 93 to the jet port 94. The inflow port 93 is provided in a portion of the gap 10 sandwiched between the impingement plate 5 and the seal plate 6. The jet port 94 is provided in a portion of the gap 10 located on the working fluid flow path 4 side from the seal plate 6 and is provided in the side part 11 so as to face the side part 12 of the flow path component 2A. ing. Other parts are the same as those of the third embodiment.

  In order to adjust the flow rate of the discharge flow 32 in the present embodiment, the number and diameter of the impingement cooling holes 53 and the cooling holes 13 and the dimensions of the seal gaps 71 and 72 may be adjusted. In this case, the flow rate can be easily adjusted if it is sufficient to change the number and diameter of the cooling holes 13 and impingement cooling holes 53 as in the above embodiments.

  In the sealing device of the present embodiment configured as described above, the cooling fluid flowing into the gap 10 via the impingement plate 5 is introduced into the cooling hole 13. The cooling fluid introduced into the cooling hole 13 is guided to the jet outlet 94 while cooling the flow path component 1E, and collides with the side portion 12 of the flow path component 2A as a forced convection cooling flow 34. As a result, the forced convection cooling flow 34 jet-cools the flow path component 2 </ b> A via the side portion 12.

  According to the present embodiment, in addition to the effects obtained in the third embodiment, as shown in the table of FIG. 6, the heat transfer coefficient and forced convection cooling of the jet collision surface equivalent to the fifth embodiment are shown. The heat transfer coefficient can be obtained. Furthermore, since the flow path component 2A can be directly cooled by the forced convection cooling flow 34, the thermal load on the flow path component 2A can be effectively reduced. Thus, the efficiency and reliability of the gas turbine can also be improved by this embodiment.

  In the description of the present embodiment, the case where the cooling hole 13 is provided in the third embodiment has been described as an example. However, the present invention is not limited to this, for example, the seal of the second embodiment. Of course, it can also be applied to the apparatus.

  In each of the above embodiments, compressed air has been described as an example of the cooling fluid. However, as the cooling fluid other than air, steam, nitrogen, or the like that is appropriately pressurized according to the pressure of the working fluid is also used. can do.

BRIEF DESCRIPTION OF THE DRAWINGS Sectional drawing of the sealing apparatus of the gas turbine which is the 1st Embodiment of this invention. The perspective view of the sealing apparatus of the gas turbine which is the 1st Embodiment of this invention. The perspective view of the sealing apparatus of the gas turbine which is the 1st comparative example of the 1st Embodiment of this invention. The top view of the sealing apparatus of the gas turbine which is the 2nd comparative example of the 1st Embodiment of this invention. The perspective view of the sealing apparatus of the gas turbine which is the 2nd comparative example of the 1st Embodiment of this invention. The comparison table of the cooling effect of the sealing device of each embodiment concerning the 1st comparative example, the 2nd comparative example, and the present invention. Sectional drawing of the sealing apparatus of the gas turbine which is the 2nd Embodiment of this invention. The perspective view of the sealing apparatus of the gas turbine which is the 2nd Embodiment of this invention. The fragmentary sectional view of the gas turbine to which the sealing apparatus of the gas turbine which is the 2nd Embodiment of this invention is applied. FIG. 10 is a partial cross-sectional view of the first stage stationary blade 111 on the plane AA in FIG. Sectional drawing of the sealing apparatus of the gas turbine which is the 3rd Embodiment of this invention. The perspective view of the sealing apparatus of the gas turbine which is the 3rd Embodiment of this invention. Sectional drawing of the sealing apparatus of the gas turbine which is the 4th Embodiment of this invention. The perspective view of the sealing apparatus of the gas turbine which is the 4th Embodiment of this invention. Sectional drawing of the sealing apparatus of the gas turbine which is the 5th Embodiment of this invention. The perspective view of the sealing apparatus of the gas turbine which is the 5th Embodiment of this invention. Sectional drawing of the sealing apparatus of the gas turbine which is the 6th Embodiment of this invention. The perspective view of the sealing apparatus of the gas turbine which is the 6th Embodiment of this invention.

Explanation of symbols

DESCRIPTION OF SYMBOLS 1 Flow path structural member 2 Flow path structural member 3 Cooling fluid flow path 4 Working fluid flow path 5 Impingement plate 6 Seal plate 8 Recess 9 Film cooling hole 10 Gap 11 Side part 12 Side part 13 Cooling hole 21 Protrusion part 22 Protrusion part 31 Jet 32 Discharge 33 Film cooling 34 Forced convection cooling 51 Groove (for impingement plate)
52 Groove (for impingement plate)
53 Impingement cooling hole 61 Groove (for impingement plate)
62 Groove (for impingement plate)
91 Inlet 92 Outlet 93 Inlet 94 Outlet

Claims (8)

  1. A pair of flow path components that are disposed so that their sides oppose each other via a gap, and that define a flow path for working fluid and a flow path for cooling fluid;
    Two sets of grooves respectively provided on the side portions of the pair of flow path component members so as to face each other with the gap therebetween;
    Of these two sets of grooves, a plate spanned in the groove on the flow path side of the working fluid;
    A gas turbine seal device comprising: another plate having a plurality of cooling holes provided at a position of the gap, spanning a groove on the cooling fluid flow path side of the two sets of grooves. .
  2. A flow path component that defines a flow path for the working fluid and a flow path for the cooling fluid, and has a side portion having a shape in which a portion on the flow path side of the working fluid protrudes from a portion on the flow path side of the cooling fluid;
    Contrary to the shape of the side portion of the flow path component, the flow path side portion on the cooling fluid side has a side portion that protrudes from the flow path side portion of the working fluid. Another flow path component that is disposed to face the side of the path structure member with a gap therebetween and defines the flow path of the working fluid and the flow path of the cooling fluid together with the flow path structure member;
    A set of grooves provided so as to face each other through the gap on the protruding part in the side part of the flow path component member and the side part of the other flow path component member opposed to the side part;
    Another set of grooves provided on the side portion of the other flow path component member and the side portion of the flow path component member facing the other portion so as to be opposed to each other via the gap;
    A plate spanning the set of grooves;
    A gas turbine seal device comprising: another plate having a plurality of first cooling holes provided in a position of the gap, spanning the other set of grooves.
  3. The gas turbine seal device according to claim 2,
    The flow path component has a recess provided by retreating a surface on which a cooling fluid ejected from a plurality of first cooling holes of the other plate directly collides toward the flow path side of the working fluid. Gas turbine sealing device.
  4. The gas turbine seal device according to claim 2,
    The flow path component member obliquely penetrates from an inlet provided in a portion sandwiched between the two plates on the side portion to an outlet provided facing the flow path of the working fluid. A gas turbine seal device comprising a plurality of second cooling holes provided.
  5. The sealing device for a gas turbine according to claim 4,
    The gas turbine sealing device according to claim 1, wherein the plurality of second cooling holes are provided at outlets of the gap.
  6. The sealing device for a gas turbine according to claim 4,
    The gas turbine seal device according to claim 1, wherein the inlets of the plurality of second cooling holes are provided at positions deviating from the axial centers of the plurality of first cooling holes.
  7. The sealing device for a gas turbine according to claim 4,
    The gas turbine sealing device according to claim 1, wherein the second cooling hole is provided so as to be inclined so as to follow a flow direction of the working fluid in the working fluid flow path.
  8. The gas turbine seal device according to claim 2,
    The flow path component is formed from an inlet provided in a portion sandwiched between the two plates on the side portion, and a jet provided in a portion of the gap located on the flow path side of the working fluid from the plate. A gas turbine seal device comprising a plurality of third cooling holes provided so as to penetrate to the outlet.
JP2007059850A 2007-03-09 2007-03-09 Gas turbine sealing device Active JP4690353B2 (en)

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8092159B2 (en) * 2009-03-31 2012-01-10 General Electric Company Feeding film cooling holes from seal slots
RU2536443C2 (en) 2011-07-01 2014-12-27 Альстом Текнолоджи Лтд Turbine guide vane
US9759081B2 (en) * 2013-10-08 2017-09-12 General Electric Company Method and system to facilitate sealing in gas turbines
WO2019035178A1 (en) * 2017-08-15 2019-02-21 東芝エネルギーシステムズ株式会社 Turbine stationary blade row and turbine

Citations (4)

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Publication number Priority date Publication date Assignee Title
US4767260A (en) * 1986-11-07 1988-08-30 United Technologies Corporation Stator vane platform cooling means
US5088888A (en) * 1990-12-03 1992-02-18 General Electric Company Shroud seal
JP2002004805A (en) * 2000-06-08 2002-01-09 General Electric Co <Ge> Method for cooling end rail of high-pressure and low- pressure turbine composite shroud
JP2003035105A (en) * 2001-07-19 2003-02-07 Mitsubishi Heavy Ind Ltd Gas turbine separating wall

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4650394A (en) * 1984-11-13 1987-03-17 United Technologies Corporation Coolable seal assembly for a gas turbine engine

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4767260A (en) * 1986-11-07 1988-08-30 United Technologies Corporation Stator vane platform cooling means
US5088888A (en) * 1990-12-03 1992-02-18 General Electric Company Shroud seal
JP2002004805A (en) * 2000-06-08 2002-01-09 General Electric Co <Ge> Method for cooling end rail of high-pressure and low- pressure turbine composite shroud
JP2003035105A (en) * 2001-07-19 2003-02-07 Mitsubishi Heavy Ind Ltd Gas turbine separating wall

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