Ring segment of gas turbine

• US 7,033,138 B2
• Filed: 09/06/2002
• Issued: 04/25/2006
• Est. Priority Date: 09/06/2002
• Status: Expired due to Term

• Current Assignee: Mitsubishi Heavy Industries, Ltd.
• Original Assignee: Mitsubishi Heavy Industries, Ltd.
• Inventors: Laurello, Vincent, Soechting, Friedrich, Tomita, Yasuoki, Inoue, Shinichi, Isumi, Osamu, Matsuoka, Hiroshige
• Primary Examiner(s): Look, Edward K.
• Assistant Examiner(s): Edgar, Richard A.
• Application Number:
  US10/235,825
• Publication Number:
  US 20040047725A1
• Time in Patent Office: 1,327 Days
• Field of Search: 415/116, 415/139, 415/173.1, 415/171.1, 415/173.4
• US Class Current: 415/139
• CPC Class Codes: F01D 11/005 Sealing means between non relatively rotating elements
• CPC Class Codes: F01D 11/08 for sealing space between rotor blade tips and stator specially-shaped blade tips therefor F01D5/20
• CPC Class Codes: F01D 25/12 Cooling
• CPC Class Codes: F01D 25/246 Fastening of diaphragms or stator-rings
• CPC Class Codes: F05D 2240/55 Seals
• CPC Class Codes: F05D 2260/201 by impingement of a fluid

Abstract

An object of the present invention is to provide a ring segment of a gas turbine in which the temperature is maintained low, damage due to high temperature oxidation is prevented, and high temperature deformation is prevented. In order to achieve the object, the present invention provides a ring segment of a gas turbine which comprises a blade ring, a main shaft and moving blades comprising a plurality of individual units which define an annular form by being arranged around the peripheral direction of the main shaft, and disposed so that its inner peripheral surface is maintained at a constant distance from the tips of the moving blades, wherein grooves which extend along the axial direction of the main shaft of the turbine are formed upon of the individual units so as mutually to confront one another; a seal plate which is inserted into each mutually confronting pair of the grooves so as to connect together the adjacent pair of individual units; and contact surfaces which are formed at positions more radially inward than the seal plates, which extend in the axial direction and the peripheral direction and which mutually contact one another.

Claims

1. A ring segment of a gas turbine which comprises a blade ring, a main shaft and moving blades, comprising a plurality of individual units which define an annular form by being arranged around a peripheral direction of the main shaft, and disposed so that its inner peripheral surface is maintained at a constant distance from tips of the moving blades, each individual unit comprising:

grooves which extend along an axial direction of the main shaft, each groove facing a groove formed in an adjacent individual unit;

a seal plate for connecting together each adjacent pair of individual units, said seal plate being inserted into the grooves of adjacent units;

a convex side edge which is formed to be convex on a radially inward side of the seal plate so as to project a convex portion into a concave side edge of a first adjacent individual unit;

a concave side edge which is formed to be concave on the radially inward side of the seal plate so as to receive a convex side edge of a second adjacent individual unit;

contact surfaces defined on the radially inward side of the seal plate when the convex side edge of the individual unit and the concave side edge of the first adjacent individual unit are fitted together,

beveled portions of the convex side edge and concave side edge on both radially inward peripheral side surfaces of said individual unit, each beveled portion facing a beveled portion of the adjacent individual unit, both beveled portions covered by a thermal barrier coating; and

ejection apertures of a plurality of conduits including a first conduit which is open toward upstream, a second conduit which is open toward downstream, and a third conduit which is open toward the adjacent individual unit.

2. A ring segment of a gas turbine as described in claim 1, wherein a gap between each pair of individual units is greater than zero and less than or equal to 1 mm when the gas turbine is operating nominally.

3. A ring segment of a gas turbine as described in claim 1, wherein a thickness of a body of each of the individual units is greater than or equal to 1 mm and less than or equal to 4 mm.

4. A ring segment of a gas turbine as described in claim 1, wherein each individual unit comprises projections formed upon an outer peripheral surface thereof.