DEVICE FOR SEALING GAS TURBINE STATOR BLADES

Abstract: A sealing device for a gas turbine stator blade, in which a sealing pressure of an inner shroud is raised to enhance a sealing effect. An outer shroud 32 is mounted through heat insulating rings 32a and 32b on a blade ring 50, and this blade ring 50 has air holes 1 and 51, of which the air hole 1 communicates with a space 53 whereas the air hole 51 communicates with a seal tube 2. This seal tube 2 is inserted at its leading end portion 3 into the air hole 51, and a spring 6 is arranged between a projection 4 of the tube 2 and a retaining portion 5 of the air hole 51 to fix the seal tube 2 removably. Cooling air 54 flows on one side from the air hole 1 into the space 53 to cool the shrouds and the inside of a stator blade 31 until it is released from the trailing edge, and on the other hand into a cavity 36 so that the inside of the cavity 36 is kept at a high pressure without receiving a pressure loss because the tube 2 is independent of the space 53. The high pressure air from the cavity 36 flows out from seal portions 40a and 40b, as indicated by arrows S1 and S2, to prevent the inflow of the hot gas from a combustion gas passage.

Description: TECHNICAL FIELD The present invention relates to a stator stage with a sealing structure for a gas turbine, as defined by the preamble portion of claim 1. BACKGROUND ART Fig. 12 is a general block diagram of a gas turbine, which is constructed to include a compressor 150, a turbine 151 and a combustor 152. A fuel is burned in the combustor 152 with the air coming from the compressor 150 so that a hot combustion gas is fed to the turbine 151. This combustion gas flows through a combustion gas passage, in which moving blades mounted on a rotor and stator blades are alternately arranged in multiple stages, to rotate the rotor thereby to drive a power generator connected directly to the rotor. Since the turbine 151 is exposed to the hot combustion gas, on the other hand, the air from the compressor 150 is partially bled and fed to the turbine 151 to cool the stator blades, the moving blades and the rotor. Fig. 13 is a section showing a sealing air feed line to a representative stator blade of a gas turbine of the prior art, and shows the construction of the blades in the turbine 151 of Fig. 12. In Fig. 13, reference numeral 21 designates a moving blade including a platform 22, a seal plate 23 under the platform 22, two end portions 24 and 25 of the platform 22, and a blade root 26. A plurality of moving blades 21 each composed of those members are arranged in the circumferential direction of the rotor. Reference numeral 31 designates a stator blade which is arranged adjacent to the moving blade 21. Numeral 32 designates an outer shroud, and numeral 33 designates an inner shroud. Numerals 34 and 35 designate two end portions of the inner shroud 33, and numeral 36 designates a cavity under the inner shroud 33. Numeral 37 designates a seal ring retaining ring which has a labyrinth seal 37a at its end portion and which slides with respect to the rotating portion of the blade root 26 on the moving blade side. Numeral 38 designates an air hole which is formed through the seal ring retaining ring 37 to provide communication between the cavity 36 and a space at the blade root 26 of the adjoining moving blade 21. Numerals 40a and 40b designate seal portions between the platform 22 and the inner shroud 33 adjoining each other and are constructed by fitting seal members between the end portions 24 and 34, and 25 and 35. Numeral 50 designates a blade ring, on the inner side of which the outer shroud 32 of the stator blade 31 is fixed through heat insulating rings 32a and 32b. Numeral 51 designates an air hole which is formed in the blade ring 50. This air hole 51 communicates with a space 53, which is formed by the blade ring 50, the heat insulating rings 32a and 32b and the outer shroud 32, and is connected at its leading end with an air source leading from the not-shown compressor. Numeral 52 designates a seal tube which is extended from the outer shroud 32 in the stator blade 31 through the inner shroud 33. In the construction thus far described, cooling air 54 from the compressor is fed from the air hole 51 of the blade ring 50 and into a space 53. This cooling air 54 flows on one side through the seal tube 52 into the cavity 36 under the inner shroud 33. The cooling air from this cavity is blown from the air hole 38, as indicated by arrow S1, into the trailing side space of the adjoining moving blade 21 at the upstream side and further through the labyrinth seal 37a into the leading side space of the moving blade 21 at the trailing stage, as indicated by arrow S2. These cooling air flows S1 and S2 emanate from the seal portions 40a and 40b, respectively, to prevent the combustion gas from entering the inside of the inner shroud 33. On the other hand, the air having entered the space 53 cools the face of the outer shroud 32 and enters the cooling passage in the stator blade, as described with reference to Fig. 16, so that it is blown out of the holes of the trailing edge while cooling the blade inside, until it is released to the combustion gas passage. In the sealing structure thus far described, the air hole 51of the blade ring has a diameter of 2 to 50 mm, and the seal tube 52 is limited in its internal diameter by the thickness and the camber of the blades. As a result, the air to flow in is subjected to a pressure loss so that its pressure drops. In addition, the cooling air having entered the space 53 leaks from the clearances between the outer shroud 32 and the heat insulating rings 32a and 32b, as indicated by arrows S3 and S4. Here will be described one example of the pressure situations resulting from the aforementioned leakage. The cooling air 54 to flow into the air hole 51 of the blade ring 50 has a pressure of about 6 Kg/cm 2 . This pressure is lowered to about 5 Kg/cm 2 in the space 53 by the pressure loss and further to 3.5 Kg/cm 2 in the cavity 36 by the pressure loss. This pressure level is equal to the pressure of 3.5 Kg/cm 2 between the moving blade 21 and the stator blade 31 adjoining each other so that the sealing effect is deteriorated. A first problem of the sealing structure for the gas turbine stator blade of the prior art thus far described is that the cooling air fed from the air hole 51 of the blade ring 50 leaks from the clearances between the outer shroud 32 and the heat insulating rings 32a and 32b, as described hereinbefore, although it flows into the space 53 between the blade ring 50 and the outer shroud 32 and into the cavity 36 under the inner shroud 33 from the seal tube 52. On the other hand, the cooling air is subjected to the pressure loss in the seal tube 52 so that its pressure drops when it flows into the cavity 36 of the inner shroud. As a result, the difference from the pressure of the combustion gas disappears to make it difficult for the cooling air to keep a sufficient pressure as the sealing air. Fig. 14 is a section showing a stator blade of the gas turbine of the prior art, which is similar to that disclosed in US-A-5 488 825 and on which the preamble portion of claim 1 is based, and explains the cooling of the stator blade mainly although the stator blade has the same structure as that of Fig. 13. In the stator blade 31, as shown in Fig. 14, air passages 80A, 80B and 80C are sequentially formed to form a serpentine passage. Reference numeral 80D designates the trailing edge of the blade, which has a number of film cooling air holes 60. The seal tube 52 vertically extends through the stator blade 31. The inner shroud 33 has the cavity 36, into which the seal tube 52 is opened at its lower end. The seal ring retaining ring 37 retains the flange of the inner shroud 33 and the labyrinth seal 37a. The air hole 38 is formed in the retaining ring 37 to provide the communication of the cavity 36 with a space 72 between the former and the adjoining moving blade. The outer shroud 32 has a cooling air feeding hole 62. The numeral 21 designates the adjoining moving blade 21. In the stator blade thus constructed, cooling air 70 is fed from the hole 62 of the outer shroud 32 to the air passage 80A on the leading edge side of the stator blade 31 and flows at the inner side into the next air passage 80B and then at the outer side into the adjoining air passage 80C. The cooling air 70 then flows at the inner side to cool the stator blades 31 sequentially and further flows from the air holes 60 of the trailing edge 80D along the outer surfaces of the trailing edge to effect the film cooling. From the open end of the seal tube 52 of the outer shroud 32, on the other hand, cooling air 71 for the cooling operation flows from the lower end of the seal tube 52 into the cavity 36, as shown in Fig. 13, so that its portion flows from the air hole 38 formed in the cavity 36 into the space 72 between the former and the adjoining moving blade and further through the labyrinth seal 37a into a forward space 73. Thus, the cooling air flows from the seal tube 52 into the cavity 36 to keep the inside of the cavity 36 at a higher level than that in the outside combustion gas passage thereby to prevent the hot combustion gas from entering the inside. Although not shown, on the other hand, the air from the compressor passes the disc cavity and flows from the radial hole formed in the blade root 26 to the inside of the platform 22 so that it is guided to cool the moving blade 21. The gas turbine stator blade of the prior art is provided therein with the air passage for cooling, as has been described hereinbefore. This air passage is ordinarily formed into the serpentine passage, and the cooling air is fed from the outer shroud into the air passage to cool the inside of the stator blade until it is released from the trailing edge to the outside. Separately of the cooling purpose, on the other hand, the seal tube is extended through the stator blade to feed a portion of the cooling air as the sealing air from the outer shroud into the cavity of the inner shroud, which is kept at a higher pressure than that in the external combustion gas passage to prevent the hot combustion gas from entering the inside. In the stator blade cooling system thus far described, the much cooling air is fed for the cooling purpose and for the sealing purpose. The cooling air cools the stator blade and is then released from the trailing edge to the combustion gas passage. On the other hand, a portion of the cooling air is bled as the sealing air and is fed through the seal tube to the cavity so that it is released from the cavity into the spaces between the former and the adjoining front and rear moving blades. In addition to the pressure loss of the foregoing first example, therefore, a second problem of the sealing device for the gas turbine stator blade is raised from the fact that much air is consumed for the cooling and sealing purposes so that the capacity of the compressor increases to burden a serious power on the performance of the gas turbine. DISCLOSURE OF THE INVENTION In order to solve the first problem, therefore, it is an object of the invention to provide a gas turbine stator stage with a sealing structure, which is enabled to enhance the sealing effect, by reducing the air flow leaking from the outer shroud and feeding the sealing air under a sufficient pressure to the inner shroud. Another aspect of the invention is to provide a gas turbine stator stage, which has the enhanced sealing effect and which can be easily assembled and disassembled for its assembly and maintenance by adopting a removable structure for the sealing air feeding seal tube and can achieve the sealing effect with a simple structure. To solve this problem the invention provides a gas turbine stator stage with a sealing structure as defined by claim 1. Preferred embodiments are defined in the dependent claims. In the invention, the space, which is formed by the wind ring, the heat insulating ring and the outer shroud, is fed with the air from the air hole communicating with the space, and this air is guided to the cooling passage in the stator blade while cooling the face of the outer shroud and is released from the holes of the blade trailing edge while cooling the blade inside. On the other hand, the seal tube is fed with the air from the air hole communicating therewith and is independent of the space so that the air can be fed to the inner shroud without being influenced by the air flow to leak from the space through the clearance between the outer shroud and the heat insulating ring joint and with receiving little pressure loss. As a result, the cavity in the inner shroud can be kept at a higher pressure than that of the combustion gas passage to enhance the sealing effect. In a preferred embodiment, the leading end of the seal tube is removably connected to the air hole so that it can be easily inserted and fixed in and removed from the stator blade at the assembly or maintenance of the stator blade. BRIEF DESCRIPTION OF THE DRAWINGS Fig. 1 is a diagram showing the entire construction of a gas turbine plant to which a gas turbine stator stage of the invention is applied; Fig. 2 is a section showing the entirety of a sealing device for a gas turbine stator blade according to the first embodiment of the invention; Fig. 3 is a perspective view showing an assembled state of the sealing device for a gas turbine stator blade according to the first embodiment of the invention; Fig. 4 is a section showing a seal tube leading end portion of the sealing device for a gas turbine stator blade according to the first embodiment of the invention; Fig. 5 is a section showing another example of the seal tube leading end portion of the sealing device for a gas turbine stator blade according to the first embodiment of the invention; Fig. 6 is a section showing a seal tube leading end portion of a sealing device for a gas turbine stator blade according to a second embodiment of the invention; Fig. 7 is a section showing another example of the seal tube leading end portion of the sealing device for a gas turbine stator blade according to the second embodiment of the invention; Fig. 8 is a section showing an application example of Fig. 6 of the sealing device for a gas turbine stator blade according to the second embodiment of the invention; Fig. 9 is a section showing an application example of Fig. 7 of the sealing device for a gas turbine stator blade according to the second embodiment of the invention; Fig. 10 is a section showing the neighborhood of a seal ring retaining ring of the gas turbine stator blade according to the first and second embodiments of the invention; Fig. 11 is a characteristic diagram illustrating comparisons with the prior art in thermal elongations on a rotor side and a stator side by cooling a gas turbine seal ring retaining ring according to the first and second embodiments of the invention; Fig. 12 is a diagram showing a general construction of the gas turbine of the prior art; Fig. 13 is a section showing a sealing structure of the gas turbine stator blade of the prior art; and Fig. 14 is a section of the gas turbine stator blade of the prior art and shows flows of sealing air and cooling air. BEST MODE FOR CARRYING OUT THE INVENTION The invention will be described in detail in connection with its embodiments with reference to the accompanying drawings. Fig. 1 is a diagram showing a construction of the entirety of a gas turbine. As shown, the gas turbine is constructed to include a compressor 150, a turbine 151 and a combustor 152. In the combustor the fuel is burned with the air coming from the compressor so that a hot combustion gas is generated and fed to the turbine 151. On the other hand, the construction, in which the air from the compressor 150 is bled via a bleeder line 153 and fed through the turbine 151 into a rotor, moving blades and stator blades until it cools down, is identical to that of the prior art,as shown in Fig. 12. In the embodiments of the invention, on the other hand, a cooler 154 is disposed, if necessary, midway of the bleeder line 153 so that it can cool the cooling air coming from the compressor 150. This cooler 154 is used, if necessary, for cooling especially a seal ring retaining ring, as shown in Figs. 10 and 11, in the invention. Fig. 2 is a section showing a sealing device for a stator blade in the turbine 151 of the gas turbine, as described hereinbefore, and shows a first embodiment of the invention. In Fig. 2, the structure of the moving blade, as designated by the reference numerals 21 to 26, the structure of the stator blade, as designated by the numerals 31 to 38, and the entire structure of the stator blade and the moving blade, as designated by the numerals 40, 50, 51 and 53, are given the same functions as those of the prior art shown in Fig. 15. Therefore, they are quoted as they are although their descriptions are omitted. The portions featuring the invention are located at the reference numerals 1 to 6, as will be described in detail. Reference numeral 1 appearing in Fig. 2 designates an air hole which is so formed separately of the air hole 51 in the blade ring 50 as to communicate with the space 53. Numeral 2 designates a seal tube which is extended from an outer shroud 32 through the inside of a stator blade 31 and further through an inner shroud 33 and is inserted into a cavity 36. A seal tube leading end portion 3 is extended into the space 53 and is inserted into the air hole 51. Numeral 4 designates a projection fixed around the leading end portion 3 of the seal tube 2, and numeral 5 designates a retaining portion formed at the blade ring 50 on the exit side of the air hole 51 and having an enlarged radius. Numeral 6 designates a coil spring which is arranged around the seal tube leading end portion 3. When this coil spring is given an elastic force, its one end goes into the air hole 51 and is retained on the step of the retaining portion 5, and its other end is held by the projection 4 to push the projection with the elastic force thereby to fix the seal tube leading end portion 3. Fig. 3 is a perspective view showing the assembled state of the stator blade. When the stator blade 31 is to be assembled, as shown, in order to insert the seal tube 2 into the air hole 51 of the blade ring 50, the outer shroud 32 bearing the seal tube 2 and the spring 6 is covered with the blade ring 50 while inserting the seal tube 2 into the air hole 51. Next, heat insulating rings 32a and 32b are carried one by one in a circumferential direction (or in a direction R) to attach the outer shroud 32. The detachment is performed in the reversed order. In this assembly, the spring 6 is elongated by its elastic force between the projection 4 of the seal tube leading portion 3 and the enlarged retaining portion 5 of the air hole 51 so that the seal tube 2 can be fixed in the blade ring 50. Fig. 4 is a section showing the state in which the seal tube leading end portion 3 is mounted in the air hole 51. As shown, the seal tube leading end portion 3 is slightly fitted in the air hole 51 and is surrounded by the spring 6. This spring 6 is fitted with the elastic force between the projection 4 formed on the seal tube 2 and the radially enlarged retaining portion 5 in the air hole 51 of the blade ring 50 so that its elastic force fixes the seal tube 2 in the air hole of the blade ring 50. Fig. 5 is a section showing another example of the first embodiment of the state in which the seal tube leading end portion is fitted in the air hole. On the leading end of the seal tube 2, there is fitted a removable adapter 7, the leading end of which is inserted into the air hole 51 of the blade ring 50. The adapter 7 is provided with a projection 4, and the spring 6 is fitted with the elastic force between the projection and the enlarged retaining portion 5 formed in the air hole 51, to fix the seal tube with its elastic force. Thus in the example shown in Fig. 5, the seal tube 2 is fixed through the adapter 7. In the sealing device for the gas turbine stator blade thus far described according to the first embodiment, a portion of the cooling air, as bled from the compressor, flows from the air hole 1 into the space 53 which is formed by the blade ring 50, the outer shroud 32 and the heat insulating rings 32a and 32b. The air thus having flown into the space 53 cools the face of the outer shroud 32 as in the prior art, then goes into the cooling passage inside the stator blade 31 that is not shown, and blows out from the trailing edge while cooling the blade inside, as has been described in connection with the example of the prior art of Fig. 14, until it is released to the combustion gas passage. A portion of the air having entered the space 53 leaks, as indicated by arrows S3 and S4, from the clearances between the outer shroud 32 and the heat insulating rings 32a and 32b into the combustion gas passage, but exerts no influence on the pressure of the sealing air because it is independent of the lines of the sealing air hole 51 and the seal tube 2. On the other hand, the cooling air 54 flows from the air hole 51 into the seal tube 2 and goes into the cavity 36 in the lower portion. The cooling air further flows from the cavity 36 via an air hole 38, which is formed in a seal ring retaining ring 37, into the space, as indicated by arrow S1, between the adjoining moving blade 21 and stator blade 31, until it flows out to the combustion gas passage through a seal portion 40a. On the other hand, the air in the cavity 36 flows via the air hole 38 and through a labyrinth seal 37a into the space between the labyrinth seal 37a and the adjoining downstream moving blade 21 until it flows through a seal portion 40b, as indicated by arrow S2, into the combustion gas passage. Thus, the hot combustion gas is prevented, by the outflow of the sealing air from the seal portions 40a and 40b, from entering the inside of the stator blade from the combustion gas passage. Here will be described one example of the pressure state in the air passages thus far described. The cooling air 54 is at about 6 Kg/cm 2 . When the cooling air 54 flows into the air holes 1 and 51, it is subjected in the space 53 to a pressure loss by the inflow from the air hole 1 so that it takes about 5 Kg/cm 2 as in the prior art. However, the air to flow from the air hole 51 is independent of the space 53 so that it flows without any substantial pressure loss from the seal tube 2 into the cavity 36 to keep the pressure in the cavity 36 at about 5 Kg/cm 2 . In the prior art, the pressure in the cavity 36 is lowered to about 3.5 Kg/cm 2 because the air flowing from a seal tube 52 receives the pressure loss. In the first embodiment of the invention, however, the pressure in the cavity can be kept as high as 5 Kg/cm 2 . By this high pressure in the cavity 36, the air is expelled, as indicated by the arrows S1 and S2, from the seal portions 40a and 40b into the combustion gas passage, which is at about 3.5 Kg/cm 2 so that the sealing pressure is so high as to provide a sufficient sealing effect. For the assembly or disassembly of the stator blade, on the other hand, the leading end of the seal tube 2 can be easily fixed in the air hole 51 of the blade ring 50 by compressing the spring 6, by inserting the seal tube leading end slightly into the air hole 51 and by elongating the spring 6. If the structure shown in Fig. 5 is adopted, on the other hand, the attachment and detachment are facilitated by handling the adapter 7 and the spring 6. According to this fixing method using the spring 6, moreover, the thermal elongation, if any, of the seal tube 2 can be admitted by the air hole 51 against the elastic force of the spring 6 so that it can be absorbed. Figs. 6 to 9 show a sealing device for a gas turbine stator blade according to a second embodiment of the invention, which is different from the first embodiment in that a bellows 9 is used to seal the inserted portion of the blade ring 50 of the seal tube leading end portion 3 into the air hole 51. The remaining construction is identical to that of the first embodiment so that its description will be omitted. In Fig. 6, the construction of Fig. 4 is provided with the bellows 9 to seal the seal tube leading end portion 3. This bellows 9 is fixed at its upper end around the air hole 51 of the blade ring 50 by a soldering method or the like and at its lower end around the seal tube 2 likewise by the soldering method or the like. In Fig. 7, the construction of Fig. 5 is provided with the bellows 9, which is fixed at its lower end around the adapter 7. The remaining construction is identical to that of Fig. 6. In Fig. 8, on the other hand, the spring 6 and the projection 4 are eliminated from the construction of Fig. 6, but only the bellows 9 is likewise attached to the construction so that its elongation and contraction may take the action of the spring force. In Fig. 9, the spring force is likewise given to the construction of Fig. 7 exclusively by the bellows 9. In the second embodiment shown in Figs. 6 to 9, the sealing air to be fed to the seal tube 2 is more completely sealed than the first embodiment so that the sealing effect can be more enhanced. Here in this second embodiment, the description has been made on the example in which the lower end of the bellows 9 is fixed by the soldering method or the like, but the bellows 9 may be fixed by binding or elastically fastening it. Fig. 10 is an enlarged section showing the neighborhood of the seal ring retaining ring in the first and second embodiments of the invention, and shows a portion of the stator blade at the second stage. The air, as bled from the compressor 150, is cooled by the cooler 154 shown in Fig. 1. The cooling air thus cooled by the cooler 154 is introduced from the seal tube 2 of the stator blade 31 into the cavity 36 to keep the cavity at a high pressure as in the prior art while cooling the seal ring retaining ring 37. Reference letters ΔA1 and ΔA2 designate the thermal elongations in the radial direction of the front and rear stages, as confronting the seal ring mounted on the seal ring retaining ring 22, on the rotor side, and letters ΔB designate the thermal elongation of the seal ring end face, as held by the seal ring retaining ring 22, on the stationary side. Of these, the thermal elongations ΔA1 and ΔA2 are substantially equal to each other, but the thermal elongation ΔB exhibits characteristics different from those of the elongations ΔA1 and ΔA2. Fig. 11 plots the thermal elongations in the radial direction on the stationary side and the rotor side in a manner to compare the prior art, in which the seal ring retaining ring 37 is not cooled, and the invention in which the same is cooled. In Fig. 11, letters ΔB' designate a thermal elongation of the end face of the labyrinth seal 37a (or the seal ring) supported by the seal ring retaining ring 37 and plot the characteristics of the prior art, in which the seal ring retaining ring 37 is not cooled. According to these characteristics, the thermal elongation occurs after the run gradually from the initial clearance S1 and is saturated to a constant level for 4 mm or more at the rated rotation time. Letters ΔA1 and ΔA2 designate the thermal elongations of the face confronting the seal ring on the rotor side. According to these characteristics, the thermal elongation more abruptly occurs than the elongation ΔB for ten minutes after the run and then increases little by little until it is saturated at a lower level than the elongation ΔB at the rated rotation time. The elongations ΔA1 and ΔA2 exhibit the substantially equal values, and the elongation ΔA1 is located on the front stage side and is slightly larger. However, the elongations ΔA1 and ΔA2 exhibit the substantially identical characteristics. Letters ΔB designate a thermal elongation of the seal ring end face of the invention of the case the air is cooled by the cooler 154 to cool the seal ring retaining ring 37. The thermal elongation ΔB has an initial value S2 rather larger than the value S1 of the prior art. The characteristics of this thermal elongation ΔB are gentler than those of the elongation ΔB', and the thermal elongation is saturated at a lower value at the rated rotation time. The thermal elongation ΔL of a body is generally expressed by ΔL = α · L · ΔT, wherein: α indicates a coefficient of linear expansion; L indicates the length of the body; and ΔT indicates a temperature difference. Since the thermal elongation ΔL can be reduced according to the formula by reducing the temperature difference ΔT, this difference between the temperature at an assembly (or cold) time and the temperature at a running (hot) time is reduced by cooling the air by the cooler 154 to cool the seal ring holding ring 37 with the air so that the thermal elongation of the seal ring holding ring 37 can be reduced to make the ΔB smaller than the ΔB'. Reverting to Fig. 11, the thermal elongations ΔA1 and ΔA2 really fluctuate depending upon a vibration at the start or upon an error at the manufacture or assembly. If this error is designated by TL, the thermal elongation ΔB' of the prior art, for which the run has been started with the initial clearance S1, reaches the minimum clearance MCR' before ten minutes and then gradually increases up to thirty minutes, until it is saturated at 4 mm or more when the rated rotating speed is reached. On the other hand, the thermal elongations ΔA1 and ΔA2 on the rotor side increases more steeply at the start but are saturated at lower levels. At the rated rotating time, the difference from the ΔB', i.e., the clearance at the hot time takes a large value, as indicated by CR'. On the other hand, the thermal elongation ΔB of the invention has the initial clearance S2 which is set larger than the S1 of the prior art. Since the air is cooled by the cooler 154 to cool the seal ring retaining ring 37 thereby to make the temperature difference smaller than that of the prior art between the temperatures at the starting (or cold) time and at the running (or hot) time, as described hereinbefore, the thermal elongation ΔB is gentler than the ΔB' so that the minimum clearance MCR occurs after about ten minutes later than the prior art. At the rated rotating time, on the other hand, the thermal elongation is saturated at a lower level than that of the prior art so that the difference between the ΔA1 and ΔA2 at the rated rotating time, i.e., the clearance can take the value CR smaller than CR' of the prior art. In the first and second embodiments of the invention, as described hereinbefore, in addition to the aforementioned improvement in the sealing effect, the sealing air to the stator blades at the individual stages is cooled by the cooler 154 and fed to the cavity 36 to cool the seal ring retaining ring 37 so that the temperature difference between the starting time and the running time can be made lower than that of the prior art, in which the sealing air is not cooled, to reduce the clearance between the seal portions on the rotor side and the stationary side at the rated rotating time. In the aforementioned case, moreover, the clearance at the rated running time can be made smaller than that of the prior art even if the initial clearance is enlarged from the S1 to the S2, so that advantages in the design and manufacture can be achieved to improve the sealing performance. According to the invention, the air can be fed without any cavity pressure loss in the inner shroud, so that the pressure in the cavity can be kept at a higher level than that in the combustion gas passage to enhance the sealing effect. On the other hand, the seal tube is characterized by connecting it removably to the air hole in the blade ring communicating with the seal tube. With this construction, at the assembly or maintenance time of the stator blade, the leading end of the seal tube can be easily inserted into and fixed in the air hole of the blade ring and can be easily removed.

Claims: A gas turbine stator stage with a sealing structure, comprising: a blade ring (50), an outer shroud (32) fixed to an inner side of said blade ring (50) through heat insulating rings (32a,32b), a first cavity (53) defined by said blade ring (50), said outer shroud (32) and said heat insulating rings (32a,32b), wherein air is adapted to be introduced from an air source into said first cavity (53) through a first air hole (1) formed in said blade ring (50), an inner shroud (33), a stator blade (31) extending radially between said outer shroud (32) and said inner shroud (33), a second cavity (36) provided in said inner shroud (33), and a seal tube (2) extending through said outer shroud (32) and said stator blade (31); characterized in that said seal tube (2) extends through said first cavity (53), said outer shroud (32) and said stator blade (31); and air for sealing the inside of said inner shroud (33) is adapted to be introduced into said second cavity (36) from the air source through a second air hole (51) formed in said blade ring (50) separately from said first air hole (1) and communicating with said seal tube (2). A gas turbine stator stage with a sealing structure as set forth in claim 1, wherein said seal tube (2) is removably connected to said second air hole (51). A gas turbine stator stage with a sealing structure as set forth in claim 2, wherein a spring (6) is provided such that its elastic force fixes said seal tube (2) in said second air hole (51). A gas turbine stator stage with a sealing structure as set forth in claim 1, 2 or 3, wherein a adapter (7) is removably provided between a leading end of said seal tube (2) and said second air hole (51).

Inventors: AI TOSHISHIGE, AOKI SUNAO, FUKUNO HIROKI, SUENAGA KIYOSHI, TOMITA YASUOKI, YURI MASANORI, AI, TOSHISHIGE, AOKI, SUNAO, FUKUNO, HIROKI, SUENAGA, KIYOSHI, TOMITA, YASUOKI, YURI, MASANORI, AI, Toshishige, Takasago Machinery Works, AOKI, Sunao, Takasago Machinery Works, FUKUNO, Hiroki, Takasago Machinery Works, SUENAGA, Kiyoshi, Takasago Machinery Works, TOMITA, Yasuoki, Takasago Machinery Works, YURI, Masanori, Takasago Machinery Works
Applicants: MITSUBISHI HEAVY IND LTD, MITSUBISHI HEAVY INDUSTRIES, LTD.
Application year: 1998
Main classification: F01D9
IPC codes: F01D11, F01D9, F02C7