Turbine shroud segment

• US 7,186,078 B2
• Filed: 12/22/2003
• Issued: 03/06/2007
• Est. Priority Date: 07/04/2003
• Status: Active Grant

• Current Assignee: Ishikawajima-Harima Heavy Industries Company Limited
• Original Assignee: Ishikawajima-Harima Heavy Industries Company Limited
• Inventors: Tanaka, Agamu
• Primary Examiner(s): Nguyen; Hoang
• Application Number:
  US10/740,663
• Publication Number:
  US 20050002779A1
• Time in Patent Office: 1,170 Days
• Field of Search: 415/170.1, 415/173.1, 415/173.6
• US Class Current: 415/170.1
• CPC Class Codes: F01D 11/005 Sealing means between non relatively rotating elements
• CPC Class Codes: F01D 25/246 Fastening of diaphragms or stator-rings
• CPC Class Codes: F01D 5/225 by shrouding
• CPC Class Codes: F01D 9/04 forming ring or sector
• CPC Class Codes: F02C 7/28 Arrangement of seals
• CPC Class Codes: F05D 2240/11 Shroud seal segments
• CPC Class Codes: F05D 2240/57 Leaf seals

Abstract

A shroud segment for being incorporated in a gas turbine engine so as to suppress influence of hot combustion gas on a turbine case of the gas turbine engine is provided with a back plate having first and second plate portions formed in an arc shape and supported by the turbine case, a touching member integrally formed on an inner surface of the back plate for touching with a rotating turbine blade, a pair of first seal slots for receiving a pair of first spline seal plate, a pair of second seal slots for receiving a pair of second spline seal plate and a pair of seal gaps respectively communicating with the first seal slots and the second seal slots. The seal gaps are respectively provided with abutment surfaces recessed from front surfaces of the second seal slots so as to receive front ends of the first spline seal plates.

Claims

1. A shroud segment for being incorporated in a gas turbine engine so as to suppress influence of hot combustion gas on a turbine case of the gas turbine engine, comprising:

a back plate formed in an arc shape and supported by the turbine case, the back plate comprising a first plate portion and a second plate portion integrally formed on an axially front end of the first plate portion and extended radially inward;

a touching member integrally formed on an inner surface of the back plate for touching with a rotating turbine blade;

a pair of first seal slots for receiving a pair of first spline seal plates, the first seal slots being formed on circumferentially both sides of the first plate portion and extended substantially across a whole length of the first plate portion;

a pair of second seal slots for receiving a pair of second spline seal plates, the second seal slots being formed on circumferentially both sides of the second plate portion and extended substantially across a whole length of the second plate portion; and

a pair of seal gaps respectively communicating with the first seal slots and the second seal slots to allow insertion of the first spline seal plates and the second spline seal plates, the seal gaps respectively comprising abutment surfaces recessed from front surfaces of the second seal slots so as to receive front ends of the first spline seal plates to prevent the first spline seal plates from displacing from the first seal slots.

2. The shroud segment of claim 1, further comprising:

a pair of first spline seal plates inserted in the first seal slots; and

a pair of second spline seal plates inserted in the second seal slots.

3. The shroud segment of claim 1, wherein:

an angle made by a first plane parallel to the first seal slot and a second plane parallel to the abutment surface is configured to be larger than 110 degrees and smaller than 125 degrees.

4. The shroud segment of claim 1, further comprising:

a front seal connected with a front end surface of the back plate so as to seal hot combustion gas leakage from a radially inner side of the back plate to the turbine case.

5. The shroud segment of claim 4, wherein:

the front seal is configured to steadily contact with an outer band of a turbine nozzle disposed at a former stage of the shroud segment by means of elastic force thereof.

6. A shroud segment for being incorporated in a gas turbine engine so as to suppress influence of hot combustion gas on a turbine case of the gas turbine engine, comprising:

a back plate formed in an arc shape and supported by the turbine case, the back plate comprising a first plate portion and a second plate portion integrally formed on an axially front end of the first plate portion and extended radially inward;

a touching member integrally formed on an inner surface of the back plate for touching with a rotating turbine blade;

a pair of first seal slots for receiving a pair of first spline seal plates, the first seal slots being formed on circumferentially both sides of the first plate portion and extended substantially across a whole length of the first plate portion;

a pair of second seal slots for receiving a pair of second spline seal plates, the second seal slots being formed on circumferentially both sides of the second plate portion and extended substantially across a whole length of the second plate portion;

a pair of seal gaps respectively communicating with the first seal slots and the second seal slots, the seal gaps respectively comprising abutment surfaces recessed from front surfaces of the second seal slots so as to receive front ends of the first spline seal plates; and

an angle made by a first plane parallel to the first seal slots and a second plane parallel to the abutment surface is configured to be larger than 110 degrees and smaller than 125 degrees.

7. A shroud segment for being incorporated in a gas turbine engine so as to suppress influence of hot combustion gas on a turbine case of the gas turbine engine, comprising:

a back plate formed in an arc shape and supported by the turbine case, the back plate comprising a first plate portion and a second plate portion integrally formed on an axially front end of the first plate portion and extended radially inward;

a touching member integrally formed on an inner surface of the back plate for touching with a rotating turbine blade;

a pair of first seal slots for receiving a pair of first spline seal plates, the first seal slots being formed on circumferentially both sides of the first plate portion and extended substantially across a whole length of the first plate portion;

a pair of second seal slots for receiving a pair of second spline seal plates, the second seal slots being formed on circumferentially both sides of the second plate portion and extended substantially across a whole length of the second plate portion;

a pair of seal gaps respectively communicating with the first seal slots and the second seal slots, the seal gaps respectively comprising abutment surfaces recessed from front surfaces of the second seal slots so as to receive front ends of the first spline seal plates; and

a front seal connected with a front end surface of the back plate so as to seal hot combustion gas leakage from a radially inner side of the back plate to the turbine case.

8. The shroud segment of claim 7, wherein:

the front seal is configured to steadily contact with an outer band of a turbine nozzle disposed at a former stage of the shroud segment by means of elastic force thereof.