JP3426952B2 - 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. 3 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. These 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. 4 is a sectional view taken along line CC of 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. 5 is a sectional view taken along a line DD in FIG. 3 and shows a cooling passage 55 which opens from the front to the rear of the platform 50 and cooling passages 57 and 6 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 to maintaining the cooling effect and cooling of the entire platform,
In particular, a shape that allows cooling on the peripheral side surface, which is severely affected by heat, has been desired. Therefore, the present invention simplifies the path of the cooling air of the platform, simplifies the supply path of the cooling air to facilitate processing, and maintains the cooling effect of the entire platform without impairing it. It is an object of the present invention to provide a gas turbine blade platform capable of effectively cooling a gas turbine. [0010] The present invention SUMMARY OF THE INVENTION The provides the following hand stage to solve the problems described above. [0011] provided on both sides of the blade in the platform, and two cooling passages the other end communicating with one end to the leading edge passage Dodotsubasa respectively open to the platform peripheral side surface, the two A lid for closing each opening of the cooling passage,
One end of each of the two cooling passages communicates with one of the two cooling passages, and the other end of each of the cooling passages has an opening at the rear end of the platform. And a plurality of cooling holes that are open on the peripheral side surface. [0012] [0013] platform of the present invention is both side portions cooling passage provided along both side end surfaces of the platform,
Cooling air is guided and flows from the cooling passage on the leading edge side communicating with the passage of the bucket, and flows out from the opening on the rear end surface to cool both sides of the platform. Further, a large number of cooling holes are arranged in communication with one of the two side end cooling passages, for example, a cooling passage on the back side exposed to high-temperature combustion gas, and cooling air is discharged from these cooling holes to reduce heat influence. Severe side end surfaces can be effectively cooled. [0014] Moreover said platforms has no cooling passages inclined at conventional such complex, the cooling passage opening at the rear end face extending along a simple two side portions, and a short cooling holes are sequentially arranged Since it is a simple cooling system, its processing is easy. Embodiments of the present invention will be specifically described below with reference to the drawings. Figure 1 shows a gas turbine blade according to the shape condition of the present invention, an A-A sectional view in (a) is a plan view, (b) (a). In FIG. 1, reference numeral 1 denotes a platform, and 51 denotes a moving blade. Reference numerals 2 and 3 denote cooling passages, each of which extends to the left and right on the leading edge side of the moving blade 51 inside the platform 1, and has one end communicating with a passage 52 on the leading edge side of the moving blade 51, and the other end respectively. It is arranged toward both ends of the platform 1. Reference numeral 4 denotes a cooling passage, and the platform 1
The front end communicates with the cooling passage 3, and the rear end is open at the rear edge side. Further, a large number of cooling holes 5 opening toward the side face communicate with the cooling passage 4 and are arranged on the side face. Reference numeral 6 denotes a cooling passage, and the platform 1
It is pierced along the ventral side surface of the inner bucket 51,
The front end communicates with the cooling passage 2, and the rear end is arranged to be open on the rear edge side. 2a and 3a are lids, and 2a is a cooling passage 2
And 3a is inserted into the opening of the cooling passage 3 and closes the opening. This lid 2
a and 3a are for facilitating drilling of the cooling passages 2 and 3 in the platform 1 when the cooling passages 2 and 3 are machined in the platform 1.
It is only necessary to make a hole penetrating toward the passage 52 at the front edge of the platform 1 and close the opening on the side surface of the platform 1 with the lids 2 and 3, making the hole processing simple. [0021] In the platform of the form status of implementation of the above arrangement, (not shown) the cooling air 70 as well as into the interior of the blade 52 toward the through tip passageway 52 from the base of the blades 51, some of It flows into the cooling passages 2 and 3. The cooling air 70 flowing into the cooling passages 2 and 3 is 70a, 70b
, And cools the front edge of the platform 1 and flows into the cooling passages 4 and 6, respectively. The cooling air 70c that has flowed into the cooling passage 4 is successively supplied to a large number of cooling holes 5 through 7 while flowing through the passage 4.
The cooling air 70e flows out as 0d, cools the side edge on the back side of the platform 1, and the remaining cooling air 70e flows out from the opening at the rear end. In this way, the back side edge and the front edge of the platform 1 exposed to high-temperature combustion gas and severely affected by heat can be effectively cooled. The cooling air 70f that has flowed into the cooling passage 6 flows through the passage 6 as it is, flows out of the rear end opening, and cools the side end of the platform 1 on the downstream side of the combustion gas. In this case, the cooling passage 6 is not provided with a large number of cooling holes directed to the side end, and is omitted in consideration of the workability of the platform 1, and the side end is cooled only by the cooling air 70 f flowing through the cooling passage 6. The cooling of the part near the moving blade 51 is minimized. According to the above form status of implementation of the described gas turbine moving blade platform, leading cooling air 70a from the passage of the front edge of the blade 51, 70b, respectively, the platform 1 flowed in the cooling passages 4 and 6 of both side edge portions to cool, a number of cooling holes 5 disposed only on the side end portion of the strict dorsal thermal effects, these cooling holes 5 leads to the cooling air from the cooling passage 4, the side edge portion as 70d The minimum cooling passage that cools this side end by flowing out to the side and a simple cooling air flow path configuration, so that the platform does not have many complicated and inclined cooling passages 1 effectively cools the whole, plus the platform 1
This facilitates processing of the cooling system. FIG. 2 shows a gas turbine blade platform according to a configuration considered for reference in connection with the present invention;
(A) is the top view, (b) is BB sectional drawing in (a). In the figure, reference numeral 11 denotes a platform, and 51 denotes a moving blade. The moving blade 51 includes a passage 5 on the leading edge side.
2. The passages 41 and 42 are provided in the center and 43 are provided on the trailing edge side. Cooling air flows into these passages, and although not shown, some or all of these passages are communicated inside the blade. Thus, a serpentine cooling passage is formed to cool the entire moving blade. Numerals 12a and 12b denote cooling passages formed inside the platform 1, respectively. One end thereof communicates with the passage of the moving blade 52 as shown in the figure, and the other end opens to the side surface of the platform. In these cooling passages, a plurality of cooling passages 12a are arranged in parallel on the ventral side of the moving blade 51, and the same number of cooling passages 12b are arranged in parallel on the back side opposite to 12a. In the example shown, two cooling passages 12a and 12b are connected to the cooling passages 52, 41 and 43, and three cooling passages are connected to the central cooling passage 42.
Are arranged linearly in opposite directions to each other, and each of the passages 52, 4
A part of the cooling air is guided from 1, 42, and 43, flows toward both side surfaces of the platform 1, respectively, flows out of the opening of the side surface as 70 g from the cooling passage 12a and 70h from the 12b, and the entire surface of the platform 1 is uniformly distributed. Cool. In the gas turbine rotor blade platform of the embodiment examined as a reference for the above configuration, a plurality of cooling passages 12a and 12b are formed not only in the center of the platform 11 but also on both side edges thereof in parallel with each other and linearly. The arrangement cools the entire platform uniformly. Also, large side end portions of the thermal effect is effectively cooled, its workability simple regular cooling passages than disposed further cooling effect, processability both in which better. [0029] Although in the shape condition of the present invention the cooling passage 6 is shown in one embodiment, the present invention is not limited to this example, 3 if of course two or allowed
The book or the book need not necessarily be a straight line. In the embodiment examined for reference , the cooling passages 12a, 12b are provided with passages 52 , 41, 4 of the rotor blade 51 .
In the example shown, two lines are connected to 3 and three lines are connected to 42. However, only three, four, or one line may be provided for each passage if space permits. It is naturally increased or decreased according to the request. Also, the cooling passage 12
The same effect can be obtained even if a and 12b are not necessarily arranged in parallel. The gas turbine moving blade platform of the present invention according to the present invention is provided on both sides of the blade in the platform, one end to the platform circumferential side surface communicating with the other end to the leading edge passage Dodotsubasa Two cooling passages each opening, a lid closing each opening of the two cooling passages,
One end of each of the two cooling passages communicates with one of the two cooling passages, and the other end of each of the cooling passages has an opening at the rear end of the platform. Are provided with a plurality of cooling holes opened on the peripheral side surface. Such a configuration simplifies the cooling system of the platform, simplifies its processing and maintains the cooling effect of the entire platform, especially effective cooling of the side edge of the platform where thermal effects are severe. Can be. [0032]

BRIEF DESCRIPTION OF THE DRAWINGS [Figure 1] shows a gas turbine moving blade platform according to the shape condition of the embodiment of the present invention, (a) is a plan view, (b) is a A-A sectional view in (a) is there. FIGS. 2A and 2B show a platform of a gas turbine rotor blade according to a mode studied for reference in the present invention, wherein FIG. 2A is a plan view and FIG. 2B is a cross-sectional view taken along line BB in FIG. FIG. 3 is a typical internal sectional view of a conventional gas turbine blade. FIG. 4 is a reduced cross-sectional view taken along the line CC in FIG. 3; FIG. 5 is a reduced sectional view taken along the line DD in FIG. 3; [Description of Signs] 1,11 Platforms 2,3,4,6 Cooling passages 2a, 3a Lid 5 Cooling holes 12a, 12b Cooling passages 51 Blades 41,42,43,52 Passages 70a-70h 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-64-63605 (JP, A) JP-A-64-83826 (JP, A) U.S. Pat. No. 4,017,210 (US, A) U.S. Pat. No. 5,382,135 (US, A) (58) Fields investigated (Int. Cl. ⁷ , DB name) F01D 1 / 00-11 / 10 F02C 1/00-9/58

Claims (1)

(57) [Claim 1] Two blades provided on both sides of a moving blade in a platform, one end of which is communicated with a leading edge passage of the moving blade, and the other end of which is open to the peripheral side surface of the platform. A cooling passage, and a lid for closing each opening of the two cooling passages,
One end of each of the two cooling passages communicates with one of the two cooling passages, and the other end of each of the cooling passages has an opening at the rear end of the platform. And a plurality of cooling holes that are open on the peripheral side surface.