JP3453293B2 - Gas turbine blade platform - Google Patents

Description

Description: BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a gas turbine moving blade platform, which is designed to improve cooling performance. 2. Description of the Related Art FIG. 4 is an internal sectional view of a typical platform of a gas turbine moving blade, which is an example mainly used for a single-stage moving blade. In the figure, 50 is the entire platform, and 51 is a single stage rotor blade. 52 is a moving blade 5
The cooling passages 53 and 54 extending to both sides are provided in communication with the passage 52. The cooling passages 53 and 54 are respectively provided on the cooling passages 5 on both sides.
5 and 56, the passages 55 and 56 each being open at the rear end of the platform 50. At the front end of the platform 50, cooling passages 57, 58 and 59, 60 are provided on both sides, respectively. The cooling passages 57 to 60 are formed by being inclined from the lower surface to the upper surface of the platform 50. It opens at the top and blows out cooling air.
The cooling passages 61 and 6 are located behind the platform 50.
2,63 are drilled and the platform 5
0 is provided so as to be inclined from the lower surface toward the upper surface, is opened at the rear end, and blows out cooling air. Further, cooling passages 64, 65, 66, 67, and 68 are provided at the center of the platform, and are similarly provided obliquely from the lower surface of the platform toward the upper surface so as to blow cooling air to the upper surface. The outlet end is formed in a divergent shape on the upper surface to diffuse cooling air. FIG. 5 is a sectional view taken along the line CC in FIG.
5 and 56 are shown, and a state is shown in which the cooling passage 67 is formed obliquely from the lower surface of the platform 50 toward the upper surface. FIG. 6 is a sectional view taken along a line DD in FIG. 4 and shows a cooling passage 55 that opens from the front to the back of the platform 50 and cooling passages 57 and 6 that are provided diagonally.
4 to 68 are provided, and show a state in which the cooling air is blown backward and upward, respectively. In the platform 50 having the above-described structure, a part of the cooling air supplied into the moving blade 51 from the leading edge passage 52 flows through the cooling passages 55 and 56 to cool both sides of the platform 50, and to be rearward of the platform 50. And the cooling passages 57-
The cooling air is guided from the lower part of the platform 50 by flowing the cooling air from the lower part of the platform 50 to the upper surface around the front and rear ends.
Are provided obliquely so as to flow out from the lower part of the platform 50 to the upper surface. The entire platform 50 is cooled by the flow and outflow of the cooling air. [0008] As described above, in the conventional typical platform of the gas turbine rotor blade, in addition to the linear main cooling passages of the cooling passages 55 and 56,
A large number of cooling passages 57-60, 61-63, etc., which penetrate the platform 50 obliquely and have a relatively long inclined route, are provided, there are many cooling air supply paths, and the processing of the platform itself becomes complicated. Facilitate and
In addition, the cooling effect has been desired to have a shape capable of uniformly cooling the entire platform. Accordingly, the present invention provides a gas turbine which simplifies the path of the cooling air of the platform, simplifies the supply path of the cooling air to facilitate processing, and uniformly cools the entire platform to enhance the cooling effect. The task was to provide a platform for the moving blade. [0010] The present invention provides the following means for solving the above-mentioned problems. Comprising an upper and lower platform,
On both the dorsal side and the abdominal side of the bucket, both side ends are arranged close to the upper and lower platforms of the neighboring buckets in the circumferential direction, and both ends are opened between the upper and lower platforms. Form a space
A cooling passage that is perforated along both sides of the upper platform, one end of which communicates with the space at the front of the platform, and the other end of which is open at the rear end; A gas turbine blade platform comprising: a plurality of holes penetrating the upper space. In the platform of the present invention, a space is formed by the upper and lower platforms, cooling air is introduced into the space, and the entire area of the platform is cooled, and both sides of the platform are cooled by cooling passages. Cooling air flows into the space through a number of holes provided in the lower platform from the inside of the platform. The cooling air flowing into the space flows through the space, flows into cooling passages provided on both sides from the front of the upper platform, flows on both sides of the upper platform, and flows out from the rear end. As described above, the space between the upper and lower platforms, the cooling passages on both sides of the upper platform, and the configuration in which a number of holes are provided in the lower platform provide a complicated and inclined passage for the cooling system of the platform. And a simple structure improves workability, while the platform is uniformly cooled,
The cooling effect also increases. Embodiments of the present invention will be specifically described below with reference to the drawings. 1A and 1B show a platform of a gas turbine rotor blade according to an embodiment of the present invention, wherein FIG. 1A is a plan view, and FIG.
It is A section explanatory drawing. In FIG. 1, reference numeral 1 denotes an upper platform, which comprises an upper platform 1 and a lower platform 11, as shown in FIG. Numerals 2 and 3 are cavities, respectively, formed between the upper and lower platforms 1 and 11 on both sides of the rotor blade 51. Reference numerals 4 and 5 denote cooling passages, which are formed along the periphery of both side ends in the upper platform 1, extend vertically downward at the leading edge side, penetrate the upper platform 1, and communicate with the cavities 2 and 3, respectively. , 5a and open at the rear end. In FIG. 1 (b), the upper platform 1 and the lower platform 11 have both side ends respectively approaching the upper and lower platforms 1 'and 11' of the adjoining blade in the circumferential direction via seal pins 20 respectively. The lower platform 11 is provided with a large number of holes 12a, 12b penetrating into the cavities 2, 3 from the inside. FIG. 2 shows a plan view of the lower platform 11 in the above platform. As shown in the figure, a large number of holes 12a and 12b penetrating the cavities 2 and 3, respectively, are arranged on the entire surface of the lower platform 11. FIG. 3 is a sectional view taken along a line BB in FIG. 1. As shown in FIGS. 1 and 2, a cooling passage 4 is formed in the upper platform 1 in the front-rear direction. 4 is provided with a vertically lower hole 4a communicating with the inside of the cavity 2 on the leading edge side, and a number of holes 12a penetrating into the cavity 2 from the inside (rotor side) are arranged in the lower platform 11. Reference numerals 21 and 22 denote sealing plates provided before and after the platform to seal the inside. In the platform having the above configuration, the cooling air 70 flows into the cavities 2 and 3 from the holes 12a and 12b of the lower platform 11 from the inside of the moving blade, as shown in FIG. During the process of flowing to the front edge side, the walls of the cavities 2 and 3 are uniformly cooled and flow into the cooling passages 4 and 5 at both ends of the upper platform 1 through the holes 4 a and 5 a provided in the upper platform 1. I do. The cooling air flowing into the cooling passages 4 and 5 is shown in FIG.
As shown in (a), each flows toward the trailing edge, is exposed to the high-temperature combustion gas, cools the peripheral portions on both sides of the upper platform 1 that is severely affected by heat, and flows out to the trailing edge. According to the platform of the gas turbine rotor blade of the embodiment described above, the platform is constituted by the upper and lower platforms 1 and 11, and the cavities 2 and 3 are formed therebetween, and the upper platform 1 is formed.
Are provided with cooling passages 4 and 5 on both sides, and a plurality of holes 12a and 12b penetrating from the inside to the cavities 2 and 3 are arranged on the entire lower platform 11 so that the cooling air 70 is supplied from the inside of the lower platform 11. Holes 12a, 12b
Through the holes 2, 3a, and further through the holes 4a, 5a to the cooling passages 4, 5 of the upper platform 1, and flows out from the trailing edge side. With such a configuration, the entire platform has large upper and lower platforms and linear cooling passages 4, 5,
It has a simple structure including the short holes 4a, 5a, 12a, 12b, etc., and eliminates a complicated and inclined cooling passage as in the related art, thereby facilitating machining. Further, the cavities 2 and 3 are formed, and the cooling air 70 is guided into the cavities 2 and 3 by the large number of holes 12a and 12b, so that the entire upper and lower platforms 1 and 11 can be uniformly cooled. Since both ends of the upper platform 1 exposed to the high-temperature combustion gas are effectively cooled by the cooling passages 4 and 5, the cooling effect of the entire platform 11 is increased. Incidentally, the large number of holes 12a, 1
2b are linearly arranged in each row in FIG. 2, but the present invention is not limited to this example.
The arrangement may be staggered or irregular, and may be arranged so as to maintain uniformity over the entire surface of the platform 11. The platform of the gas turbine rotor blade according to the present invention comprises upper and lower platforms. On both the back side and the abdomen side of the rotor blade, both ends are circumferentially adjacent to each other. The upper and lower platforms are disposed in proximity to the upper and lower platforms, forming an open space between the upper and lower platforms at both ends thereof. A cooling passage that communicates with the space at the front of the vehicle, and the other end of the cooling passage is open at the rear end. Features. With such a configuration, since a simple cooling structure of the space, the short hole, and the linear cooling passage is provided, the processing of the cooling structure and the processing of the platform itself are facilitated, and the platform is uniformly cooled, and the cooling effect is improved. improves.

BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 shows a gas turbine bucket according to an embodiment of the present invention, (a) is a plan view of an upper platform,
(B) is AA sectional explanatory drawing in (a). FIG. 2 is a plan view of a lower platform of the gas turbine bucket according to the embodiment of the present invention. FIG. 3 is a reduced sectional view taken along the line BB in FIG. 1; FIG. 4 is a typical sectional view of a conventional gas turbine blade. FIG. 5 is a reduced cross-sectional view taken along the line CC in FIG. 4; FIG. 6 is a reduced sectional view taken along the line DD in FIG. 4; [Description of Signs] 1 Upper platform 2, 3 Cavity 4, 5 Cooling passage 4a, 5a Hole 11 Lower platform 12a, 12b Hole 51 Moving blade 70 Cooling air

──────────────────────────────────────────────────続 き Continuation of the front page (72) Inventor Yasushi Tomita 2-1-1 Shinhama, Arai-machi, Takasago City, Hyogo Prefecture Inside the Takasago Works, Mitsubishi Heavy Industries, Ltd. (56) References JP-A-11-22404 (JP, A) JP-A-59-176401 (JP, A) JP 10-508077 (JP, A) JP 9-505378 (JP, A) UK Patent Application Publication 2050529 (JP, A) GB, A) French Patent Application Publication No. 2316440 (FR, A1) U.S. Pat. No. 4,729,791 (US, A) (58) Fields investigated (Int. Cl. ⁷ , DB name) F01D 1/00-11/10

Claims (1)

(57) [Claims 1] The upper and lower platforms are composed of upper and lower platforms, and on both sides on the back side and on the abdomen side of the blade, both ends are circumferentially adjacent to each other. The upper and lower platforms are disposed in proximity to each other to form an open space at both ends thereof , and are formed along the periphery of both sides of the upper platform, and one end is formed in front of the platform in the space. A cooling passage, the other end of which is open to the rear end, and a number of holes formed in the lower platform and penetrating from the bottom surface of the platform to the upper space. Blade platform.