Gas turbine cooled stationary blade
First Claim
1. A gas turbine cooled stationary blade comprising an outer shroud, an inner shroud and an insert of a sleeve shape, having air blow holes, inserted into an interior of the blade between said outer and inner shrouds, the blade being constructed such that cooling air entering said outer shroud flows through said insert to be blown through said air blow holes and to be further blown outside of the blade through cooling holes provided passing through a blade wall of the blade as well as to be led into said inner shroud for cooling thereof and to be then discharged outside, wherein a blade wall thickness in an area of 75% to 100% of a blade height of a blade leading edge portion of the blade is made thicker toward said insert than a blade wall thickness of other portions of the blade;
- the blade is provided therein with a plurality of ribs arranged up and down between 0% and 100% of said blade height on a blade inner wall on a blade convex side, said plurality of ribs extending in a blade transverse direction and protruding toward said insert;
said outer and inner shrouds, respectively, are provided therein with cooling passages arranged in shroud both side end portions on blade convex and concave sides of said respective shrouds so that cooling air may flow therethrough from a shroud front portion, or a blade leading edge side portion, of said respective shrouds to a shroud rear portion, or a blade trailing edge side portion, of said respective shrouds to be then discharged outside through openings provided in the shroud rear portion; and
said inner shroud is further provided therein with a plurality of cooling holes arranged along said cooling passages on the blade convex and concave sides of said inner shroud, said plurality of cooling holes communicating at one end of each hole with said cooling passages and opening at the other end in a shroud side end face so that cooling air may be blown outside through said plurality of cooling holes.
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0 Petitions
Accused Products
Abstract
Gas turbine cooled stationary blade is improved in the structure of a blade and outer and inner shrouds to enhance cooling efficiency and to prevent occurrence of cracks due to thermal stresses. Blade (1) wall thickness between 75% and 100% of blade height of a blade leading edge portion is made thicker and blade (1) wall thickness of other portions is made thinner, as compared with a conventional case. Protruding ribs (4) are provided on a blade (1) convex side inner wall between 0% and 100% of the blade height. Blade (1) trailing edge opening portion is made thinner than the conventional case. Outer shroud (2) is provided with cooling passages (5a, 5b) for air flow in the shroud both side end portions. Inner shroud (3) is provided with cooling passages (9a, 9b) for air flow and cooling holes (13a, 13b) for air blow in the shroud both side end portions. By the blade (1) structure and the shroud (2, 3) cooling passages (5a, 5b, 9a, 9b) and cooling holes (13a, 13b), cooling effect is enhanced and cracks are prevented from occurring.
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Citations
7 Claims
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1. A gas turbine cooled stationary blade comprising an outer shroud, an inner shroud and an insert of a sleeve shape, having air blow holes, inserted into an interior of the blade between said outer and inner shrouds, the blade being constructed such that cooling air entering said outer shroud flows through said insert to be blown through said air blow holes and to be further blown outside of the blade through cooling holes provided passing through a blade wall of the blade as well as to be led into said inner shroud for cooling thereof and to be then discharged outside, wherein a blade wall thickness in an area of 75% to 100% of a blade height of a blade leading edge portion of the blade is made thicker toward said insert than a blade wall thickness of other portions of the blade;
- the blade is provided therein with a plurality of ribs arranged up and down between 0% and 100% of said blade height on a blade inner wall on a blade convex side, said plurality of ribs extending in a blade transverse direction and protruding toward said insert;
said outer and inner shrouds, respectively, are provided therein with cooling passages arranged in shroud both side end portions on blade convex and concave sides of said respective shrouds so that cooling air may flow therethrough from a shroud front portion, or a blade leading edge side portion, of said respective shrouds to a shroud rear portion, or a blade trailing edge side portion, of said respective shrouds to be then discharged outside through openings provided in the shroud rear portion; and
said inner shroud is further provided therein with a plurality of cooling holes arranged along said cooling passages on the blade convex and concave sides of said inner shroud, said plurality of cooling holes communicating at one end of each hole with said cooling passages and opening at the other end in a shroud side end face so that cooling air may be blown outside through said plurality of cooling holes. - View Dependent Claims (2, 3, 4, 5, 6, 7)
- the blade is provided therein with a plurality of ribs arranged up and down between 0% and 100% of said blade height on a blade inner wall on a blade convex side, said plurality of ribs extending in a blade transverse direction and protruding toward said insert;
Specification
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- Resources
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Current Assigneemitsubishi hitachi power systems, ltd. (Mitsubishi Heavy Industries, Ltd.)
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Original AssigneeMitsubishi Heavy Industries, Ltd.
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InventorsIto, Eisaku, Shirota, Akihiko, Kuwabara, Masamitsu, Tomita, Yasuoki
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Granted Patent
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Time in Patent OfficeDays
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Field of Search
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US Class Current415/115
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CPC Class CodesF01D 5/187 Convection coolingF01D 9/041 using blades F01D5/148 take...F05D 2240/81 Cooled platformsF05D 2260/22141 using fins or ribs
