JP2004301115A - Sealing construction and sealing device of turbine tail pipe - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To provide the sealing construction of a turbine tail pipe and a sealing device for general purpose which are markedly excellent in sealing performance. <P>SOLUTION: In the sealing structure of the turbine tail pipe, clearance between turbine tail pipes is blocked with an edge surface of the sealing device 10, in which a plurality of long quadrilateral thin plates are laminated to bundle and fix the other long side. The clearance between a turbine tail pipe 5 and a shroud 6 is blocked with the thin plate flat surface of the sealing device 10, in which a plurality of long quadrilateral thin plates are laminated to bundle and fix the other long side. <P>COPYRIGHT: (C)2005,JPO&NCIPI

Description

  The present invention relates to a seal device, and more particularly to a seal structure suitable for sealing a transition piece of a prime mover or a turbine combustor.

  As a part to be sealed of a gas turbine, there is a seal for a gap between a transition piece and a shroud of a combustor, and a seal device applied to the seal part is required to follow a relative movement between the two and maintain a sealing function. I have.

  As a seal structure of a gas turbine transition piece, for example, there is one disclosed in Japanese Patent Application Laid-Open No. 2000-257762, which includes a transition piece seal 17 provided on a flange 15a of a turbine transition piece 15 and a shroud 16 as shown in FIG. Is sealed by a brush seal 18 in which a large number of linear wires are densely provided.

JP-A-2000-257762 (FIG. 4)

  Working fluids such as gas turbines have high temperatures and high pressures, and a narrow gap is provided for the mounting of internal components in consideration of thermal expansion. Therefore, it is important to prevent leakage because of various adverse effects. For this purpose, there is a demand for a sealing device which is inexpensive and has excellent sealing properties and durability.

  The present invention proposes a turbine tailpipe sealing structure and a general-purpose sealing device that have significantly improved sealing performance as compared with the conventional brush seal.

  The present invention employs the following means (1) to (12) in order to solve the above problems.

  (1) A turbine characterized in that a gap in a turbine tail tube portion is closed by the other end surface of a sealing device in which a plurality of long quadrangular thin plates are stacked and one of the long sides is fixed in a bundled state. The sealing structure of the transition piece, the sealing device can secure the rigidity that can withstand the desired turbine airflow pressure by adjusting the number of thin plates, and even if the turbine transition piece vibrates and comes into contact with the thin plate, The sheet is flexed to avoid damage and the gap is always kept to a minimum seal.

  The gap of the turbine transition piece means a gap between the side surfaces of the exit portion of the turbine transition piece as well as a gap between the turbine transition piece and the shroud.

  (2) The thin plate flat surface of the seal device in which a gap in the turbine tail tube portion between the turbine tail tube and the shroud is fixed in such a manner that a plurality of long quadrangular thin plates are stacked and one of the long sides is bundled. A seal structure of a turbine transition piece characterized by being closed by a seal device.By adjusting the number of thin plates, the sealing device can secure rigidity that can withstand a desired turbine airflow pressure, and the turbine transition piece and the like vibrate. Even if the thin plate abuts against the thin plate, the thin plate bends to avoid damage, and the gap is always kept to a minimum seal.

  (3) The sealing device is provided on the other end of a shield member having one end detachably fixed to one end of the turbine transition piece or the shroud. The sealing structure of the turbine transition piece of the above, the sealing device can secure the rigidity that can withstand the desired turbine airflow pressure by adjusting the number of the thin plates, and the turbine transition section vibrates and contacts the thin plate. However, the sheet is flexed to avoid damage and the gap is always kept to a minimum. Further, by removing the shield member, repair and replacement of the sealing device can be easily performed.

  (4) The turbine transition piece according to any one of (1) to (3), wherein one long side of the sealing device is provided along an edge of any one of the turbine transition pieces. The gap is sealed in a state where the gap is closed by a long quadrilateral plane of the thin plate.

  (5) When providing the sealing device, the thin plate is installed so that the other long side of the thin plate is inclined toward the high-pressure atmosphere side of the turbine tail tube portion. The seal structure of any one of the turbine tail pipes described above, wherein the thin plate is constantly pressed in a direction in which the gap dimension is reduced (the low-pressure atmosphere side) by the high-pressure atmosphere pressure, so that the seal gap is reduced and the sealing property is further enhanced. Become.

  (6) The seal structure for a turbine transition piece according to any one of (1) to (5), wherein a slit is provided at an appropriate position on the other end edge side of the thin plate.

  (7) A sealing device in which a plurality of quadrilateral thin plates are stacked and one side of the thin plates is fixed in a bundled state, and the other side of the thin plate is freely bent, and the flat surface of the thin plate is a seal. A sealing device characterized by a pressure receiving surface, wherein a plurality of thin plates are stacked and bundled, so that required rigidity is maintained, and there is a multiple sealing action of the thin sheets and a follow-up action accompanying the bending thereof. .

  In order to make the flat surface of the thin plate a pressure receiving surface for the sealing pressure, the sealing device may be installed so that one side is on the high-pressure atmosphere side and the other is on the low-pressure atmosphere side with the front and back surfaces of the thin plate interposed therebetween.

  (8) The sealing device according to (7), wherein the one side is provided along one edge of the member that forms the gap to be sealed, thereby closing the gap to be sealed. In addition, the gap to be sealed is closed with a quadrilateral plane of a thin plate, and sealing can be performed.

  (9) A sealing structure provided at a site where a pressure difference is generated between the front and back surfaces of two members constituting the gap to be sealed, wherein the other side of the sealing device thin plate is installed so as to be inclined toward the high pressure atmosphere side. The seal structure according to the above (8), characterized in that:

  (10) A method of remodeling a turbine tailpipe, wherein the sealing apparatus according to the above (7) is replaced or additionally provided with a sealing apparatus already provided in a turbine tailpipe portion.

  (11) A laminated thin plate static sealing device characterized in that leakage of fluid from a gap is prevented by a static sealing device having a structure in which thin plates are laminated.

  (12) A seal structure wherein the seal device according to (7) or (11) is provided in a gap to be sealed of a gas turbine, a steam turbine, or a jet engine.

  According to the first aspect of the present invention, the gap in the turbine tail tube portion is closed by the other end surface of the sealing device in which a plurality of long quadrangular thin plates are laminated and one of the long sides is fixed in a bundled state. A seal structure for a turbine transition piece characterized by the fact that the sealing device can secure rigidity that can withstand a desired turbine airflow pressure by adjusting the number of thin plates, and can also achieve thermal expansion and vibration of the turbine transition piece and the like. Therefore, even if the turbine transition piece and its mating member abut on the thin plate, the thin plate bends and the gap size is always kept to a minimum seal, the thin plate is not damaged, and the high-temperature combustion gas (turbine Air flow) is reduced to about several percent.

  According to the second aspect of the present invention, the gap in the turbine tail section between the turbine tail pipe and the shroud is fixed in a state where a plurality of long quadrangular thin plates are stacked and one of the long sides is bundled. A seal structure of a turbine transition piece, which is closed by the thin plate flat surface of a seal device.The seal device can secure rigidity that can withstand a desired turbine airflow pressure by increasing or decreasing the number of the thin plates. Even if the shroud or the like comes into contact with the thin plate due to thermal expansion or vibration of the transition piece or the like, the thin plate bends and the gap dimension is always kept to a minimum, the thin plate is not damaged, and the high-temperature combustion gas ( The leakage rate of the turbine airflow is suppressed to about several percent.

  According to a third aspect of the present invention, one long side of the seal device is connected to the other end of a shield member having one end detachably fixed to one end of the turbine transition piece or the shroud. 3. The sealing structure for a turbine tailpipe according to claim 2, wherein the sealing device can secure rigidity enough to withstand a desired turbine airflow pressure by adjusting the number of thin plates, and can secure a turbine tail. Even if the tube portion vibrates and comes into contact with the thin plate, the thin plate bends, so that the gap dimension is always kept to a minimum seal, and the air flow leakage rate in the turbine tail tube portion is suppressed to about several percent. . Further, by removing the shield member, repair and replacement of the sealing device can be easily performed.

  The invention described in claim 4 is characterized in that one long side of the seal device is provided along one edge of the turbine tail tube portion. Wherein the gap in the turbine tail section is sealed in a state where the gap is closed by the entire surface of the long rectangular plane of the thin plate.

  The invention according to claim 5 is characterized in that, when the sealing device is provided in the turbine tail section, the other long side of the thin plate is installed so as to be inclined toward the high pressure atmosphere side of the turbine tail section. The turbine tail pipe seal structure according to any one of claims 1 to 4, wherein the thin plate is constantly pressed in a direction (a low pressure atmosphere side) in which a clearance dimension is reduced by a high pressure atmosphere pressure, and is securely and firmly. Sealed.

  According to a sixth aspect of the present invention, there is provided a turbine according to any one of the first to fifth aspects, wherein a slit or a hole for enhancing flexibility is provided at an appropriate position of the thin plate. The transition piece seal structure prevents damage to the sealing device due to contact with the turbine transition piece member.

  The invention according to claim 7 is a seal device in which a plurality of quadrangular thin plates are stacked and one side of the thin plates is fixed in a bundled state, and the other side of the thin plate is freely bent, A sealing device characterized in that a flat surface of the thin plate is a pressure receiving surface for sealing pressure, and since a plurality of thin plates are stacked and bundled, rigidity that can withstand a required sealing pressure can be secured, and multiple thin plates can be secured. There is a high sealing performance effect due to the sealing action and the follow-up action accompanying the deflection.

  The invention according to claim 8 is characterized in that one side of the sealing device according to claim 7 is provided along one edge of one member constituting the gap to be sealed to close the gap to be sealed. The gap to be sealed is closed over the entire surface of the quadrilateral plane of the thin plate group.

  The invention according to claim 9 is a seal structure provided at a site where a pressure difference is generated between the front and back surfaces of two members constituting a gap to be sealed, wherein the other long side of the thin plate of the sealing device is a high pressure atmosphere side. The sealing structure according to claim 7 or 8, wherein the tip of the thin plate is always pressed against the member to be sealed by high-pressure atmospheric pressure, and is securely and firmly sealed. You.

  The invention according to claim 10 is a method for remodeling a turbine tailpipe, wherein the sealing apparatus according to claim 7 is replaced or additionally provided with a sealing apparatus already provided in a turbine tailpipe portion, By remodeling, it is possible to reduce airflow leakage in the turbine tail section.

  According to an eleventh aspect of the present invention, there is provided a laminated thin plate static seal device characterized in that leakage of fluid from a gap is prevented by a static seal device having a structure in which thin plates are laminated. Sealing can be achieved by forming a thin plate shape that matches the front shape and closing the seal gap with the thin plate. Further, the number of thin plates to be laminated may be increased or decreased in proportion to the sealing pressure, and the sealing device can cope with a wide range of pressure to be sealed.

  According to a twelfth aspect of the present invention, there is provided a seal structure in which the seal device according to the seventh or eleventh aspect is provided in a gap to be sealed of a gas turbine, a steam turbine, or a jet engine. By forming the shape in conformity with the shape of the gap to be sealed (quadrilateral or ring shape), it can be applied to sealing devices for various uses and has high versatility.

  A first embodiment of the sealing device according to the present invention will be described with reference to FIGS.

  FIG. 1A is a front view of a sealing device (assembled product), and FIGS. 1B and 1C are front views of two types of thin plates (a thin plate slit 1 and a thin plate slit 2) constituting the sealing device. .

  2 (A), 2 (B) and 2 (C) are cross-sectional views of three types of sealing devices, wherein (1A) is (A), (1B) is (B), and (1C) is (C). Shows an example of specific dimensions (unit: mm).

  For example, in FIG. 2A, a numerical value of 12 indicates that the length of the short side of the sealing device is 12 mm, and a numerical value of 4 in FIG. Each dimension is 4 mm, and the numerical values described in (1B) and (1C) of FIG. 2 are notational descriptions similar to (1A).

  The sealing device 1 shown in FIG. 1 is a sealing device 1 in a case where the gap to be sealed has a long quadrilateral shape and has a slight arc in the longitudinal direction. It is made to be a seal gap.

  The thin plates 2 and 3 of the sealing device 1 are made of stainless steel having a thickness of 0.1 mm. If a plurality of thin stainless steel plates having such a thickness are stacked and bundled, the function (sealing property) required for the sealing device 1 is obtained. Flexible and restoring properties that can achieve the above-mentioned requirements and prevent interference damage).

  The sealing device 1 uses thin plates 2 and 3 having different slit positions. Leakage from a plurality of slits 2a and 3a provided in the thin plates 2 and 3 is different from that of the thin plates 2 and 3 having different slit positions. Is prevented by alternately overlapping.

  A large number of thin plates 2 and 3 are laminated to form a laminated thin plate group 1c in a state where the four sides thereof are aligned, and the base end side (one long side of the thin plate) is sandwiched between a pair of fasteners 1b and rivets 1a. It is fixed, and the distal end side of the laminated thin plate group 1c is configured to bend freely.

  In FIG. 1, reference numerals 2b and 3b denote insertion holes for the rivets 1a, each of which is provided with four holes.

  Although the present sealing device 1 is long in the longitudinal direction, the thin plates 2 and 3 are provided with slits 2a and 3a at equal intervals in the longitudinal direction, respectively. Flexibility is increased, which is suitable not only for linear gaps to be sealed but also for curved gaps including arcs as shown in FIG.

  It is preferable that the slits 3a and 2a be provided in the thin plates inside the laminated thin plate group 1c from the viewpoint of sealing properties. Of course, as shown in FIG. 6, a slit may not be provided.

  The self-sealing property by the differential pressure is used for the sealing property. As shown in FIGS. 2A, 2B, and 2C, the tip side (the other side of the thin sheet) of the laminated sheet group 1c is placed on the high-pressure atmosphere side K of the gap to be sealed. If the long side is provided so as to be inclined, the leading end of the laminated thin plate group 1c is always urged in the direction pressed against the sealing surface S2 due to the differential pressure from the low pressure atmosphere side T, so that blow-through is not caused. In addition, flutter vibration of a thin plate can be prevented.

  Further, by appropriately changing the inclination angle, the sealing surface pressure and the flexibility can be adjusted. Flexibility can also be adjusted by the thickness of the thin plate, the effective seal length, and the slit width.

  When the present seal device 1 is installed in the gap to be sealed, the base end fixing portion 4 on one side of the seal device 1 is provided along one edge of one member constituting the gap to be sealed, and the gap to be sealed is formed. The gap to be sealed may be closed over the entire surface of the quadrilateral plane such as the thin plates 2 and 3 to perform sealing.

  Generally, stainless steel or a heat-resistant alloy is used as the material of the seal thin plates 2 and 3, but other materials such as a ceramic plate may be used depending on the application depending on the temperature.

  In the present sealing device 1, since a plurality of thin plates 2 and 3 are stacked and bundled, required rigidity is maintained, blow-through does not occur, and sealing can be reliably performed by the multiple sealing action of the plurality of thin plates.

  Further, even if the sealed gap member thermally expands and vibrates and comes into contact with the sealing device 1, the thin plate bends and follows, and the clearance between the tips of the thin plates 2 and 3 and the sealed gap member is always minimized. In addition, the sealing performance is maintained and the sealing device 1 is not damaged.

  The number of laminated thin plates 2 and 3 may be increased or decreased in proportion to the seal ambient pressure to which the sealing device 1 is applied.

  The present sealing device 1 has a simple structure in which only a plurality of thin plates are stacked, and the manufacturing cost is low. In addition, since a plurality of thin plates are sealed in a multiplex manner, the sealing properties are excellent. Also, since the stress is absorbed by the bending of the thin plate, the durability is excellent.

  In FIG. 14, holes 1d are provided in the thin plates inside the laminated thin plate group 1c instead of the slits of the sealing device 1 in FIG. 1 (A). And bends to follow lower fluid pressures.

  A first embodiment of a seal structure for a turbine transition piece according to the present invention will be described with reference to FIGS. FIG. 3 is a configuration diagram showing the entire gas turbine combustor, in which 5 is a turbine tailpipe, 6 is a shroud, A is a combustor, B is a vehicle compartment, C is a pilot fuel nozzle, and D is a main combustion nozzle. , E indicate a bypass pipe, F indicates a bypass valve, and G indicates an arrow indicating the flow direction of the high-temperature combustion gas.

  A range surrounded by Y in FIG. 3 is a turbine transition piece, and the turbine transition piece is constituted by a turbine transition piece 5 and a shroud 6 connected thereto. FIG. 4 is an enlarged view of a range surrounded by Y in FIG. 3. In FIG. 4, reference numeral 5 denotes a turbine transition piece connected to the upstream combustor A, 6a and 6b denote outer and inner shrouds connected to the turbine transition piece 5, 7 Denotes a shield member which is continuously provided so as to close a gap between the turbine transition piece 5 and the shroud 6, and is detachably fixed to the flange 5 a of the turbine transition piece 5 by a bolt 8.

  The sealing device 10 provided on the upper side of FIG. 4 is shown in FIG. 5 (A), and the lower sealing device 10 is shown in FIG. 5 (B). No slit is provided.

  The sealing device 10 shown in FIG. 4 is formed by laminating a plurality of long quadrilateral thin plates and fixing one long side thereof in a bundled state, and the other end surface closes a gap in the turbine tail tube portion. In.

  2A, one long side (fixed side) of the thin plate of the sealing device 10 of the type shown in FIG. 2A is fixed to the other end of the shield member 7.

  6 is a view of the turbine transition piece 5 viewed from the downstream side. FIG. 7A is an enlarged sectional view taken along the line MM of FIG. 6, and FIG. 7B is a view of the line NN of FIG. FIG. 8 is an arrow view taken along the line LL of FIG.

  As shown in FIGS. 6, 7, and 8, the seal device 10 includes a turbine transition piece 5 and adjacent turbine transition pieces 5c and 5d, in addition to the gap between the outer shroud 6a and the inner shroud 6b. , And the gap around the turbine transition piece 4 is completely sealed by the sealing device 10. In FIG. 8, 15A is a cover member on the combustor side.

  The sealing device 10 includes a thin plate group 10a in which ten SUS405 thin plates having a thickness of 0.1 mm are stacked, and one of the long quadrangular thin plates is fixed in a bundled state on one long side base end side. Thus, each of the thin plates on the other long side end side can be freely bent individually. The sealing device 10 is the same as that shown in FIG.

  According to the sealing device 10 configured as described above, only one thin plate has a rigidity that cannot withstand the atmospheric pressure of the turbine tail tube portion. However, since many thin plates are stacked, the entire flat surface of the thin plate is Can be secured by the thin plate group 10a to withstand the atmospheric pressure applied to the substrate.

  In addition, since each thin plate bends, the seal clearance (gap between the tip of the thin plate and the surface of the member to be sealed) is always kept to a minimum, and multiple seals are performed by each thin plate, and the sealing performance is high.

  When the sealing device 10 is fixed to the shield member 7, the other long side of the thin plate group 10a is fixedly installed (30 degrees) to the high pressure atmosphere side of the turbine tail section, and the thin plate is fixed to the high pressure atmosphere. The pressure on the surrounding side K is always pressed toward the direction in which the gap dimension is reduced, that is, the low pressure atmosphere side T, so that the sealing can be performed more reliably and the occurrence of blow-through is prevented.

  The shield member 7 on the back surface side of the thin plate group 10a is provided with an inclined surface 7a having the same inclination angle α (30 degrees) as that of the thin plate group 10a, so that the tip of the thin plate group 10a does not enter the gap S side. In combination with the above, the occurrence of blow-by is prevented.

  The seal clearance between the end of the thin plate group 10a of the seal device 10 and the plane of the shroud 6 is set to a seal clearance of about 0 to 0.1 mm in order to minimize leakage of the high-temperature combustion gas G. Due to the small seal clearance, a phenomenon occurs in which the tip of the thin plate group 10a hits the shroud 6 due to thermal expansion and vibration accompanying the operation of the gas turbine (combustor). Since the plate thickness is about 1 mm, even if the tip of the thin plate group 1a abuts on the shroud 6, each thin plate is absorbed by bending, and the leading end of the thin plate is always along the surface of the shroud 6, so that the turbine tail tube portion is formed. The seal clearance of the gap S is always maintained at a minimum size and the thin plate group is not damaged.

  Also, in the above embodiment, the shield member 7 can be easily removed by loosening the bolt 8 shown in FIG. 4, and repair and remodeling can be easily performed by replacing the shield member 7 with a new sealing device fixed. obtain.

  A second embodiment of the seal structure for a turbine transition piece according to the present invention will be described with reference to FIG. In the present embodiment, the gap S between the shield member 7 and the shroud 6 is closed by a sealing device 10b. The sealing device 10b is fixed straight, and the height of the sealing device 10b increases toward the low pressure side T on the plane of the shroud 6. This is provided with an inclined surface 6b.

  A third embodiment of the seal structure for a turbine transition piece according to the present invention will be described with reference to FIG. In the present embodiment, the gap S between the shield member 7 and the shroud 6 is closed by a sealing device 10b, and the thin plate group 10d of the shielding device 10b is installed orthogonal to the plane of the shroud 6. Thus, even if it is orthogonally installed, sealing can be performed.

  A fourth embodiment of the seal structure for a turbine transition piece according to the present invention will be described with reference to FIG. In the present embodiment, the gap S between the shield member 7 and the shroud 6 is closed by a sealing device 10c, and the inclination angle of the thin plate group 10e of the sealing device 10c is set according to the first embodiment shown in FIG. The shroud 6 is provided with an inclined surface 6b rising on the low-pressure atmosphere side T on the plane of the shroud 6. When the inclined surface 6b is provided in this manner, similarly to the case where the thin plate group 10e is inclined, a differential pressure is applied to the plane on the high pressure atmosphere side K of the thin plate group 10e, and the flat surface between the tip of the thin plate group 10e and the shroud 6 is formed. Acts to narrow the seal clearance constituted by

  A first embodiment of the seal structure according to the present invention will be described with reference to FIG. In the present embodiment, the sealing device 11 is fixedly disposed between the gaps S1 formed by the members to be sealed 19 and 20. In FIG. 12, 11a is a group of laminated thin plates, and 11b is for sandwiching the thin plates for bundling. 11c, fixing bolts, K indicates a high-pressure atmosphere side, and T indicates a low-pressure atmosphere side. In FIG. 12, the end of the laminated thin plate group 11a may be fixedly arranged so as to be inclined toward the high-pressure atmosphere side K.

  A second embodiment of the sealing device according to the present invention will be described with reference to FIG.

  The sealing device according to the present embodiment is configured by laminating a large number of quadrilateral thin plates into a laminated thin plate group 12a, and fixing a central portion thereof in a bundled state with a pair of flat plates 13 and fixing bolts 14. Both long sides of 12a are sealing devices 12 that bend freely, and can seal at both ends.

  The sealing device 12 is, like the above-described sealing devices 1, 10, 10a, 10c, and 11, such that both flat surfaces of the thin plate lamination group 12a face the high-pressure atmosphere K and the low-pressure atmosphere side T of the gap to be sealed. Install.

  The above-described sealing devices 1, 10, 10a, 10c, 11, and 12 can be easily attached to the member to be sealed by a holding member or a general fixing means such as welding and bolts. If the sealing device is deteriorated in its sealing performance due to aging, replace it with the above-mentioned sealing device 1, 10, 10a, 10c, 11, or 12, or additionally install the existing sealing device without removing it. If this is the case, it is easy to remodel the turbine transition piece or the seal structure for general use.

  Note that the shape of the thin plate of the sealing device may be a shape and a size that match the gap to be sealed or the gap, and need not necessarily be a quadrilateral as described above. For example, when the gap to be sealed or the front shape of the gap is circular, the sealing device may be a semicircle or a quarter circle, and may be a sealing device in which a plurality of thin plates are stacked so as to form a circular shape as a whole.

Further, the tip on the side where the thin plate bends may be formed along the surface of the member to be sealed, and if the surface of the member to be sealed has a curved surface, the thin plate has a tip shape along the curved line. In short, the clearance between the tip of the thin plate and the surface of the member to be sealed should be minimized.
According to each of the above embodiments, the sealing pressure applied to the plane of the laminated thin plate is received by the bending force inherent to the laminated thin plate, and leakage from gaps and gaps is prevented by performing multiple sealings with individual laminated thin plates. It can be reliably prevented, and the sealing performance is high.

  The above-described sealing devices 10, 10a, 10c, 11, 12 and the laminated thin plate static sealing device 1 can be used as sealing devices in various fields, and are provided in a gap to be sealed of a gas turbine, a steam turbine, or a jet engine. Can be done.

FIG. 1 is a front view showing a first embodiment of a sealing device according to the present invention. FIG. 3 is a cross-sectional view showing a first (A), a second (B), and a third (C) embodiment of the sealing device according to the present invention. It is a block diagram of the gas turbine combustor explaining the seal structure of the turbine transition piece according to the present invention. FIG. 4 is an enlarged view of a Y part in FIG. 3. (A), (B) is a front view of the sealing device used in FIG. FIG. 1 is a front view showing a first embodiment of a seal structure for a turbine transition piece according to the present invention. 7A is an enlarged sectional view taken along the line MM of FIG. 6, and FIG. 7B is an enlarged sectional view taken along the line NN of FIG. 6. FIG. 7 is a side view taken along line LL of FIG. 6. It is a perspective view showing a 2nd embodiment of the seal structure of the turbine tail pipe concerning the present invention. It is a perspective view showing a 3rd embodiment of the seal structure of the turbine tail pipe concerning the present invention. It is a perspective view showing a 4th embodiment of the seal structure of the turbine tail pipe concerning the present invention. It is a perspective view showing a 1st embodiment of a seal structure concerning the present invention. It is a perspective view showing a 2nd embodiment of the seal device concerning the present invention. It is a perspective view showing other embodiments of a seal device concerning the present invention. It is sectional drawing explaining the seal structure of the conventional turbine tail pipe.

Explanation of reference numerals

1, 10, 10b, 10c, 11, 12 Sealing device 2, 3 Thin plate 4 Base end fixing part 5 Turbine tail tube 6 Shroud 7 Shield member K High pressure atmosphere side T Low pressure atmosphere side

Claims (12)

The other end surface of the sealing device in which a plurality of long quadrangular thin plates are laminated and one of the long sides is fixed in a bundled state, the gap of the turbine tail tube portion is closed, Seal structure. The gap in the turbine tail tube portion between the turbine tail tube and the shroud is closed by the thin plate flat surface of the sealing device in which a plurality of long quadrangular thin plates are stacked and one of the long sides is fixed in a bundled state. The seal structure of a turbine transition piece characterized by the following. 3. A long side of the sealing device is provided at the other end of a shield member one end of which is detachably fixed to one end of the turbine transition piece or the shroud. 3. The seal structure for a turbine tail pipe according to item 1. The seal structure for a turbine transition piece according to any one of claims 1 to 3, wherein one long side of the seal device is provided along an edge of one member of the turbine transition piece section. . The said thin device is installed so that the other long side of the said thin plate may incline to the high pressure atmosphere side of the said turbine tail part at the time of providing the said sealing apparatus, The Claim 1 characterized by the above-mentioned. Seal structure of turbine tailpipe. The seal structure for a turbine transition piece according to any one of claims 1 to 5, wherein a slit is provided at an appropriate position on the other end side of the thin plate. A sealing device in which a plurality of quadrilateral thin plates are stacked and one side of one of the thin plates is fixed in a bundled state, and the other side of the thin plate is freely bent, and the flat surface of the thin plate receives a sealing pressure. A sealing device characterized by being a surface. The sealing structure according to claim 7, wherein the one side is provided along one edge of the member that forms the gap to be sealed to close the gap to be sealed. A sealing structure provided at a site where a differential pressure is generated between the front and back surfaces of two members constituting a gap to be sealed, wherein the other side of the sealing device thin plate is installed so as to be inclined toward a high-pressure atmosphere side. The seal structure according to claim 8, wherein A method for remodeling a turbine tailpipe, wherein the sealing apparatus according to claim 7 is replaced or additionally provided with a sealing apparatus already provided in a gap between the turbine tailpipe portions. A laminated thin plate static seal device characterized in that leakage of fluid from a gap is prevented by a static seal device having a structure in which quadrilateral thin plates are laminated. A seal structure, wherein the seal device according to claim 7 or 11 is provided in a gap to be sealed of a gas turbine, a steam turbine, or a jet engine.

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