Turbine blade and gas turbine

• US 20040009066A1
• Filed: 07/11/2002
• Published: 01/15/2004
• Est. Priority Date: 07/11/2002
• Status: Active Grant

• Current Assignee: mitsubishi hitachi power systems, ltd. (Mitsubishi Heavy Industries, Ltd.)
• Original Assignee: Mitsubishi Heavy Industries, Ltd.
• Inventors: Tomita, Yasuoki, Kuwabara, Masamitsu, Hada, Satoshi, Masada, Junichiro, Soechting, Friedrich
• Granted Patent: US 6,742,991 B2
• Time in Patent Office: Days
• US Class Current: 416/96R
• CPC Class Codes: F01D 5/186 Film cooling F01D5/187 takes precedence
• CPC Class Codes: F01D 5/188 with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
• CPC Class Codes: F01D 5/189 the insert having a tubular cross-section, e.g. airfoil shape
• CPC Class Codes: F05D 2250/70 Shape
• CPC Class Codes: F05D 2260/202 by film cooling

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.

Claims

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.

2. A turbine blade according to claim 1, wherein the communication means comprises a plurality of bypass holes that are formed to penetrate through the rib in its thickness direction.

3. A turbine blade according to claim 1, wherein the communication means comprises at least one slit that is formed to penetrate through the rib in its thickness direction.

4. A turbine blade according to claim 1, wherein the communication means is arranged in either a rear side or a front side, which has a good heat transmission in the turbine blade body, and is also arranged substantially in parallel with the axial line of the turbine blade body in the vertical direction.

5. A turbine blade according to claim 2, wherein the communication means is arranged in either a rear side or a front side, which has a good heat transmission in the turbine blade body, and is also arranged substantially in parallel with the axial line of the turbine blade body in the vertical direction.

6. A turbine blade according to claim 1, wherein the communication means is arranged in a rear side and a front side substantially in parallel with the axial line of the turbine blade body in the vertical direction, and wherein the communication means is formed to impart a great influence to impingement cooling in either the rear side or the front side that has a good heat transmission.

7. A turbine blade according to claim 2, wherein the communication means is arranged in a rear side and a front side substantially in parallel with the axial line of the turbine blade body in the vertical direction, and wherein the communication means is formed to impart a great influence to impingement cooling in either the rear side or the front side that has a good heat transmission.

8. A turbine blade according to claim 4 or 5 further comprising a partition wall that is arranged between the rib and the insert arranged in the trailing-edge side, thus providing a separation between the cooing space in the rear side and the cooling space in the front side.

9. A turbine blade according to claim 6 or 7 further comprising a partition wall that is arranged between the rib and the insert arranged in the trailing-edge side, thus providing a separation between the cooing space in the rear side and the cooling space in the front side.

10. A gas turbine using the turbine blade according to any one of claims 1 to 3, comprising:

a turbine having the turbine blade;

a compressor for compressing combustion air; and

a combustion chamber for combining the combustion air with fuel to burn, thus producing high-temperature combustion gas.

11. A gas turbine using the turbine blade according to claim 4 or 5, comprising:

a turbine having the turbine blade;

a compressor for compressing combustion air; and

a combustion chamber for combining the combustion air with fuel to burn, thus producing high-temperature combustion gas.

12. A gas turbine using the turbine blade according to claim 6 or 7, comprising:

a turbine having the turbine blade;

a compressor for compressing combustion air; and

a combustion chamber for combining the combustion air with fuel to burn, thus producing high-temperature combustion gas.

13. A gas turbine using the turbine blade according to claim 8 or 9, comprising:

a turbine having the turbine blade;

a compressor for compressing combustion air; and

a combustion chamber for combining the combustion air with fuel to burn, thus producing high-temperature combustion gas.