Abstract: In a cooled gas turbine stationary blade, both steam cooling and air cooling are utilized to reduce the amount of cooling air. In the stationary blade having outer and inner shrouds 1, 21 and steam passages 10A, 10B, 10C, 10D and 10E which are communicated with each other and in which a sealing air feed tube 2 passes through a central portion thereof, steam covers 3, 4 are provided in the outer shroud 1, and steam S is introduced from a steam feed port 5. The steam S passes through serpentine passages 10A to 10E and is recovered from the steam outlet 12 after cooling the central portion of the outer shroud 1 by means of an impingement plate 8. A portion of the steam of the passage 10A is introduced from the impingement plate 25 to a steam sump 24 to cool the central portion of the inner shroud 21 and pass through the passage 10D to be recovered from the steam outlet port 12.

Abstract: A cooled platform for a gas turbine moving blade which enables the platform to be cooled when the moving blade is cooled by steam. The moving blade is provided with a plurality of steam passages. Steam is introduced from the steam passage at the trailing edge portion, flows in a serpentine passage composed of other steam passages to cool the blade, and flows out to a blade root portion from a base portion of the steam passage at the leading edge portion, being recovered. Part of steam flowing into the platform from the base portion of the steam passage at the trailing edge portion enters first and second steam passages in the platform. On one side, the steam passes through first, third, and fourth steam passages, and on the other hand, the steam passes through second, fifth, and sixth steam passages. The steam is recovered together with the steam having cooled the blade at the base portion of steam passage at the leading edge portion.

Abstract: In the present invention, seal air passes through a tube extending in a stationary blade from an outside shroud to an inside shroud, flows into a cavity to keep the pressure in the cavity high so as to seal the high-temperature combustion gas, and is discharged to a passage. Part of cooling air flows into an air passage to cool the leading edge portion, passes through the peripheral portion of the inside shroud to cool the same, and is discharged to a passage. The remaining cooling air flows into a passage, passes through a serpentine cooling flow path consisting of air passages having turbulators, and is discharged through air cooling holes formed at the trailing edge. The cooling air passing through the passage at the leading edge portion cools the peripheral portion of the inside shroud as well as the leading edge portion of blade, by which the cooling efficiency is increased.

Abstract: A gas turbine rotor blade has a plurality of first cooling holes for the flow of a cooling gas bored in a blade portion along its lengthwise direction and a plurality of second cooling holes for flow of the cooling gas bored in a shroud along its plane direction so as to communicate with the first cooling holes, and is constructed such that the cooling gas can flow in a uniform distribution. The plurality of the first cooling holes 3 for flow of the cooling gas are bored in the blade portion 2 and the plurality of the second cooling holes 5 for flow of the cooling gas are bored in the shroud 1 along its plane direction. The second cooling holes 5 communicate with the first cooling holes 3, hole to hole, via two-step holes 4, and the second cooling holes 5 are bored alternately on the dorsal side and the ventral side of the rotor blade.

Abstract: A gas turbine blade having a platform and a turbine wheel plate, in which cooling passages are arranged in a plurality of rows and connected to one another in a blade trunk section of a moving blade and a supply-side passage and a discharge-side passage are formed in a blade root section. The gas turbine blade comprises a pocket having an inlet and an outlet formed in the blade root section. The supply-side passage is connected to one of the cooling passages and the inlet of the pocket, the outlet of the pocket is connected to another of the cooling passages, and the discharge-side passage is connected to one of the cooling passages other than the ones connected individually to the supply-side passage and the pocket.

Abstract: In a cooled stationary blade assembly for a gas turbine, an interior of a blade and an inner shroud are cooled by steam to eliminate the use of air cooling. Steam passages 33A, 33B, 33C, 33D, 33E and 33F are provided in the stationary blade 30. The cooling steam 39 is introduced from the steam passage 33A on the front edge side through an outer shroud and passes, in order, through the steam passages 33B, 33C, 33D, and 33E to flow into the steam passage 33F at the rear edge side to cool the interior of the blade, and is recovered through the outer shroud from the upper portion of the steam passage 33F. A portion of the steam from the steam passage 33A is introduced into the inner shroud 31, enters to steam passages 20 from a steam introduction passage 22, branches to the right and left through both end portions, and flows out into the steam passage 33F at the rear edge from a steam discharge passage 21.

Abstract: A gas turbine cooled blade has leading edge turbulators. A rounded tip portion of the leading edge portion cooling passage (3) is approximated by a triangular cooling passage (1) having orthogonal turbulators (11, 12) and a smoothly curved rear portion thereof of the leading edge portion cooling passage (3) is approximated by a square cooling passage 2 having oblique turbulators (13, 14).

Abstract: A gas turbine rotor, in which a plurality of discs having teeth of a bevel gear are juxtaposed to engage the teeth and are integrally fastened by a bolt extending through the discs, so that the discs may be cooled by feeding cooling air to the air passages of the individual discs sequentially at the running time, is provided whereby the cooling air is prevented from leaking by means having no wear.

Abstract: A seal plate at the platform portion of a gas turbine moving blade. The seal plate is inserted in a gap between the adjacent platforms at each end portion of a seal pin to prevent air from leaking to the outside. A groove is provided at each of four corners of the end portion of platform of the moving blade, and the seal plate is inserted to cover the gap so as to extend the end portions of the adjacent platforms, by which the gap between the platforms is blocked. A seal pin and end seal pins are inserted between the platforms to seal this portion. However, there is a gap at the end portions, so that cooling air leaks from the lower part of platform. Since the seal plate is inserted in the groove to block the gap, the sealing property is increased.

Abstract: Seal plates for gas turbine stationary blade inner shrouds are made in a double cross type seal structure with a view to enhance sealing ability. Seal plates 1, 2 are mutually lapped and disposed in a turbine axial direction between inner shrouds 12 of stationary blades 11. End portion seal plate 5 is lapped on an end portion of the seal plate 2 and end portion seal plate 6 is lapped under an end portion of the seal plate 1. All these seal plates are fitted with their side end portions being inserted into groove 9a provided in the inner shrouds 12. Seal plates 3, 4 and seal plates 7, 8 engaged with the seal plates 3, 4 are also fitted between flange portions of the inner shrouds 12 with their side end portions being inserted into grooves 10a, 10b and grooves 9b, 9c, respectively.

Abstract: In the present disclosure, an air pipe extends through a stationary blade between outer and inner shrouds. Further, an air passage is directed to a lower portion of the stationary blade and is communicated with the air pipe so that a serpentine cooling passage is formed. The air enters a cavity from the air passage and is discharged to a gas passage through an air hole, a passage and a seal. Thus, the cavity is sealed at a high pressure. Cooling air is supplied from the air passage to a rotating blade through a cooling air hole, a cooling air chamber, a radial hole and a lower portion of a platform. The stationary blade is cooled by the air through the air passage. The cooling air can be supplied to the rotating blade at a low temperature and a high pressure as they are. Accordingly, the air can be also supplied to the rotating blade when a rotor is cooled by vapor.

Abstract: A mechanism for cooling the platform for the drive blades of a gas turbine uses a simple configuration which reliably cools the platform. The mechanism includes cooling channels in the interior of the platform which open out from one of the cooling air channels for cooling the turbine blades and which exit the platform through the edge nearest the tail. Cooling channels in the platform open out from the entrance to blade cooling channels, travel from the head of the blade along the blade sides, and exit through the edge near the tail of the blade. This structure diverts a portion of the cooling air entering the blade from the cooling channel in the base in order to cool the platform. Cooling air channels may extend from an enclosed air space below the platform to the upper surface of the platform at the front or rear side of the blade. Air channels may also extend on the rear of the turbine blade obliquely from the underside of the platform to the trailing edge of the platform.

Abstract: A gas turbine comprises: a first closed circuit in which cooling gas is supplied to a casing, allowed to pass through stationary blades, and removed to the outside of casing after cooling the stationary blades; a second closed circuit in which cooling air is supplied to the casing, allowed to pass through moving blades, and removed to the outside of casing after cooling the moving blades; a cooler for cooling the cooling gas in the first and second closed circuits; and a booster for pressurizing and circulating the cooling gas cooled by the cooler.

Abstract: A cooling steam circulation passage for a gas turbine rotor (30) having turbine discs (41.about.47) are composed of center line bores (73.about.77) open at an axial end of the rotor and extending through a central portion of the rotor; a steam inlet-outlet pipe (79) coaxially disposed therein so as to define an annular passage (81) for cooling steam at an outer side; steam cavities (89a, 89b) defined between and by facing side surfaces of said turbine discs; steam cavities (91a, 91b) each defined at non-facing side surface portions of said turbine discs (41, 43); axial steam holes (61, 63) formed to extend through the turbine discs and including a partition tube (99); and radial steam holes (97, 103a, 103b, 105, 107) extending from each of the steam cavities (91a, 101, 89a) to mounting portions for the rotor blades.

Abstract: A gas turbine stationary blade unit in which two stationary blades are formed in a single segment by divided shrouds functions to lessen the occurrence of cracks. Two stationary blades 1a, 1b are fixed to an outer shroud and an inner shroud, respectively. Each shroud is divided into two sections 2a, 2b and 3a, 3b. Flanges 4a, 4b are provided to connect the section together by bolts via boltholes 7. Likewise, flanges 5a, 5b are provided to form a similar connection or joint. If the two stationary blades 1a, 1b are fixed in a single segment by the shrouds which are not divided, a restraining force becomes larger, local stress occurs due to thermal stress and the frequency of crack occurrence increases. However, since the shrouds are divided respectively into two parts and jointed together by bolts, the crack occurrence is lessened. Also, pinholes are provided in opposing faces at the divided portion of the shrouds.

Abstract: The present disclosure provides a gas turbine blade in which the tip end thereof is cooled effectively to decrease the metal temperature for the prevention of burning and the temperature gradient of blade metal is decreased to prevent the occurrence of cracking. In the gas turbine blade provided with a cooling passage therein, a protrusion is provided inwardly of the peripheral walls of the blade, which define the blade profile and the protrusion is positioned on the outer surface of blade tip end wall directly above a cooling passage within the blade.

Abstract: There is provided a cooled stationary blade of a gas turbine in which the portions which can be cooled sufficiently by air are air-cooled, and the portions which are difficult to cool by air are steam-cooled, by which high temperatures can be overcome. In a stationary blade 1, there is formed a serpentine passage 3 in which cooling steam flows and an air passage 10 adjacent to the trailing edge portion and separated from the serpentine passage 3. Also, an outside shroud 4 is formed with an air cooling passage 16 at the outer edge portion and a steam impingement cooling portion 17 and an air impingement cooling portion 18 on the inside of the air cooling passage 16. An inside shroud 11 is provided with an air cooling passage 19 at the outer edge portion and shaped holes 20 formed on the inside of the air cooling passage 19. The air flowing out through the shaped holes 20 performs film cooling.

Abstract: The present invention relates to a gas turbine cooled moving blade in order to cool the gas turbine using steam alone. In the moving blade, two cavities are installed in the lower part of the moving blade root section of the moving blade, a steam inlet is located in one cavity, and a steam outlet is installed in the other cavity. Steam is charged from the steam inlet and passes through a serpentine cooling passage consisting of a plurality of steam passages, and discharged to the steam outlet and collected. Bypasses are located near the base of the moving blade in the middle of each steam passage, so that cold steam on the leading edge side can be led into the bypass, mixed with the hot steam which comes from the tip section side and goes into the next downstream section of the steam passage, and flows to an upstream portion of the steam passage, thereby equalizing the steam temperature and cooling the steam over the entire range from the upstream to downstream of the steam flow.

Abstract: A gas turbine rotating blade comprises a serpentine passage provided in the blade width direction in plural rows in a blade profile portion except the portion near the trailing edge having a small blade thickness, a steam cooling passage provided around the outer periphery of a platform, an air passage provided in the blade width direction in the vicinity of the trailing edge of blade profile portion, an impingement plate provided under the platform on the inside of the steam cooling passage, slot holes formed so as to branch off from the air passage and be directed to the trailing edge, and slits formed in the platform above the impingement plate. Therefore, the blade profile portion is cooled by the steam passing through the serpentine passage and the air passing through the air passage, so that the cooling construction is not complicated, and cooling is performed effectively. For the platform, the outer periphery thereof is cooled by steam and the inside thereof by air effectively.

Abstract: The invention relates to a cooled shroud in a gas turbine stationary blade which is able to flow a cooling air in the entire area of an inner shroud for cooling thereof. Three stationary blades are fixed to the inner shroud 2, a cover 13, 14 is provided to form a space 21 and space 22a, 22b and 22c, respectively. The cooling air is introduced through an independent air passage 3A of a leading edge of each stationary blade into the spaces 22a, 22b and 22c and is flown therefrom through a tunnel 18 and air reservoirs 19-2, 19-3 and 19-4 to be blown out of a trailing edge while cooling surfaces of the shrouds and the trailing edges. Also, a portion of the cooling air from the space 22b is flown into the space 21 through a tunnel 11, a leading edge side passage 12 and an endmost tunnel 11 and is then blown out of the trailing edge through a tunnel 18 and an air reservoir 19-1, so that the leading edge portion, the endmost portion and the endmost trailing edge portion are cooled.