Division wall and shroud of gas turbine

• US 20020090296A1
• Filed: 12/26/2001
• Published: 07/11/2002
• Est. Priority Date: 01/09/2001
• Status: Active Grant

• Current Assignee: Mitsubishi Heavy Industries, Ltd.
• Original Assignee: Mitsubishi Heavy Industries, Ltd.
• Inventors: Torii, Shunsuke, Inoue, Shinichi, Fujikawa, Tatsuaki, Kuwabara, Masamitsu, Shiozaki, Shigehiro, Magoshi, Ryotaro, Tomita, Yasuoki, Morii, Yoshiyuki, Ohshima, Kotaro
• Granted Patent: US 6,893,215 B2
• Time in Patent Office: Days
• US Class Current: 415/169.1
• CPC Class Codes: F01D 11/005 Sealing means between non relatively rotating elements
• CPC Class Codes: F01D 11/006 Sealing the gap between rotor blades or blades and rotor
• CPC Class Codes: F01D 11/008 by spacer elements between the blades, e.g. independent interblade platforms

Abstract

The division wall is made up of a plurality of division wall sections forming a passage wall of high temperature gas which are connected in the direction of arrangement of blades to form a wall surface having a roughly circular cross section as a whole, a gas flow restricting structure for preventing high temperature gas from passing through a gap formed at a connecting portion between the division wall sections in the flow direction of the high temperature gas from the opening on the upstream side of the high temperature gas in the gap, or a gas flow restricting structure for preventing the high temperature gas from being embraced in the gap, for example, a sealing member formed into a prism having a T-shape cross section as a whole composed of a plane portion as a sealing portion and a projected portion for filling the gap is provided.

Claims

1. A division wall of a gas turbine, comprising:

a plurality of division wall sections connected in the direction of arrangement of blade of the gas turbine and forms a wall surface having a roughly circular cross section as a whole, the division wall sections being fixed to an outer end or an inner end of a respective blade of the gas turbine, or being arranged while interposing a predetermined space between the outer end of the respective blade to form a passage wall for high temperature gas together with a blade surface of the respective blade; and

a gas flow restricting structure which prevents the high temperature gas from passing through a gap formed at a connecting portion between the division wall sections in a flow direction of the high temperature gas from an opening on the upstream side of the high temperature gas in the gap.

2. The division wall according to claim 1, wherein the blade is a stationary blade and the division wall is a shroud.

3. The division wall according to claim 1, wherein the blade is a moving blade and the division wall is a platform.

4. The division wall according to claim 1, wherein the blade is a moving blade and the division wall is a division ring provided in a compartment while interposing a certain space between a tip end of the moving blade.

5. The division wall according to claim 1, wherein the gas flow restricting structure is a sealing member formed into a projection shape filling the gap so as to prevent the high temperature gas from leaking outside the passage wall.

6. The division wall according to claim 1, wherein the gas flow restricting structure is a shielding panel which closes the opening on the upstream side of the high temperature gas in the gap.

7. The division wall according to claim 1, wherein the gas flow restricting structure is such that a ship lap with respect to the flow direction is formed on at least the upstream side of the high temperature gas in the connecting portion of the division wall sections.

8. The division wall according to claim 1, the division wall further comprising a cooling air blowoff structure for blowing cooling air into the gap.

9. The division wall according to claim 8, wherein a blowoff opening for blowing the cooling air is formed in a side wall surface of the gap.

10. The division wall according to claim 8, wherein a blowoff passage for blowing the cooling air is formed in the sealing member provided in the gap so as to prevent the high temperature gas from leaking outside the passage wall.

11. A shroud of a gas turbine, comprising:

a division ring provided in a compartment while interposing a certain space between a tip end of a moving blade of the gas turbine, a stationary blade is provided on the back side of the moving blade, and a cooling air passage for cooling the division ring is formed in the division ring,

wherein a front end portion of the shroud opposing to an opening of the back side of the cooling air passage is formed at an angle so that an air film is formed at the front end portion by the cooling air blown from the opening.