Turbine blade and gas turbine
First Claim
1. A turbine blade comprising:
- a turbine blade body;
a plurality of film cooling holes that are arranged on exterior walls of the turbine blade body;
at least one rib having a plate-like shape that is arranged substantially perpendicular to a center line connecting between a leading edge and a trailing edge in a plane substantially perpendicular to an axial line of the turbine blade body in a vertical direction, so that an overall interior space of the turbine blade body is partitioned into at least two cavities by the at least one rib;
a plurality of inserts, each of which has a hollow shape and a plurality of impingement holes, wherein the inserts are each arranged in the cavities in such a way that a cooling space is formed between an exterior surface of the insert and an interior surface of the turbine blade body, and wherein cooling air introduced into the inserts is forced to flow into the cooling space through the impingement holes so that the turbine blade body is subjected to impingement cooling, while the cooling air spurts out through the film cooling holes of the turbine blade body to form film layers around the turbine blade body, so that the turbine blade body is subjected to film cooling; and
a communication means that is formed with the rib to provide a communication between the cavity arranged in a leading-edge side and the cavity arranged in a trailing-edge side.
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Accused Products
Abstract
A turbine blade applicable to a gas turbine has a turbine blade body having film cooling holes, the interior space of which is partitioned into two cavities by a rib. Hollow inserts each having impingement holes are respectively arranged in the cavities to form cooling spaces therebetween. Communication is ensured between the cavities by a communication means, so that the impingement cooling is interrupted with respect to the prescribed side having a good heat transmission in the turbine blade body. A partition wall is further arranged between the rib and the insert arranged in the trailing-edge side, thus providing a separation between the cooling spaces respectively arranged in the rear side and front side. Thus, it is possible to noticeably reduce the amount of cooling air in the turbine blade body; and it is possible to reduce temperature differences entirely over the turbine blade body as small as possible.
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Citations
13 Claims
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1. A turbine blade comprising:
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a turbine blade body;
a plurality of film cooling holes that are arranged on exterior walls of the turbine blade body;
at least one rib having a plate-like shape that is arranged substantially perpendicular to a center line connecting between a leading edge and a trailing edge in a plane substantially perpendicular to an axial line of the turbine blade body in a vertical direction, so that an overall interior space of the turbine blade body is partitioned into at least two cavities by the at least one rib;
a plurality of inserts, each of which has a hollow shape and a plurality of impingement holes, wherein the inserts are each arranged in the cavities in such a way that a cooling space is formed between an exterior surface of the insert and an interior surface of the turbine blade body, and wherein cooling air introduced into the inserts is forced to flow into the cooling space through the impingement holes so that the turbine blade body is subjected to impingement cooling, while the cooling air spurts out through the film cooling holes of the turbine blade body to form film layers around the turbine blade body, so that the turbine blade body is subjected to film cooling; and
a communication means that is formed with the rib to provide a communication between the cavity arranged in a leading-edge side and the cavity arranged in a trailing-edge side. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13)
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Specification