Tip clearance control for turbine blades

• US 10,208,617 B2
• Filed: 12/14/2015
• Issued: 02/19/2019
• Est. Priority Date: 12/16/2014
• Status: Active Grant

• Current Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Inventors: Jones, Simon Lloyd, Lewis, Leo V.
• Primary Examiner(s): Shanske, Jason
• Assistant Examiner(s): Adjagbe, Maxime
• Application Number:
  US14/967,997
• Publication Number:
  US 20160169027A1
• Time in Patent Office: 1,163 Days
• CPC Class Codes: F01D 11/24 by selectively cooling-heating stator or rotor components
• CPC Class Codes: F01D 25/10 Heating, e.g. warming-up before starting
• CPC Class Codes: F01D 25/12 Cooling
• CPC Class Codes: F01D 25/24 Casings modified for heating or cooling F01D25/14; Casing parts, e.g. diaphragms, casing fastenings casings for rotary machines or engines in general F16M ; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045
• CPC Class Codes: F01D 5/02 Blade-carrying members, e.g. rotors rotors of non-bladed type F01D1/34; stators F01D9/00 ; selecting particular materials F01D5/28
• CPC Class Codes: F01D 5/12 Blades specially adapted for radial flow machines or engines F01D5/04; blade roots F01D5/30; rotors with blades adjustable in operation F01D7/00; stator blades F01D9/02
• CPC Class Codes: F05D 2220/32 in gas turbines
• CPC Class Codes: F05D 2260/201 by impingement of a fluid

Abstract

A carrier segment of a carrier section for circumscribing an array of circumferentially spaced turbine blades of a gas turbine engine, the blades being disposed radially inwardly of a turbine casing, the carrier segment including a carrier wall disposed radially inwardly of the casing and radially outwardly of the turbine blades, and the carrier wall including one or more portions facing the casing, wherein at least one of the one or more portions of the carrier wall is provided with one or more impingement apertures therein for passage therethrough of air of a predetermined temperature, heating air, from a feed source into impingement onto the turbine casing. The application of heating air onto the casing during transient stages of enhanced engine power, e.g. during step climbs, results in better matching of radial expansion of the casing relative to the turbine blades, thereby enabling improved blade tip clearance control.

Claims

1. A carrier segment of a carrier section for circumscribing an array of circumferentially spaced turbine blades of a gas turbine engine, the blades being disposed radially inwardly of a turbine casing, the carrier segment comprising:

a first impingement carrier wall disposed radially inwardly of the turbine casing and radially outwardly of the turbine blades, the first impingement carrier wall including a first aperture for passage of air,

a second impingement carrier wall disposed radially inwardly of the first impingement carrier wall and radially outwardly of the turbine blades, the second impingement carrier wall including a second aperture for passage of air,

an extension section extending axially, relative to a longitudinal axis of the engine, from the first impingement carrier wall,

a first intermediate chamber disposed between the first impingement carrier wall and the turbine casing,

a second intermediate chamber disposed between the first impingement carrier wall and the second impingement carrier wall, a carrier wall aperture being disposed in an axially forward wall defining the second intermediate chamber for passage of air into the second intermediate chamber,

a third intermediate chamber disposed between the extension section and the turbine casing, and

a support disposed between the first intermediate chamber and the third intermediate chamber such that the support separates the first intermediate chamber and the third intermediate chamber, the support being connected to the turbine casing and supporting the carrier segment,

wherein an extension section aperture is disposed between the first intermediate chamber and the third intermediate chamber for passage of air, and

wherein the extension section includes a third aperture for passage of air into the third intermediate chamber.

2. The carrier segment according to claim 1, wherein a temperature of the air passed through the first aperture and onto the turbine casing is such that the turbine casing is heated thereby.

3. The carrier segment according to claim 1, wherein the second impingement carrier wall is integrally formed with a remainder of the carrier segment.

4. The carrier segment according to claim 1, wherein the first impingement carrier wall is substantially parallel to the turbine casing.

5. The carrier segment according to claim 1, wherein the first aperture includes one or more apertures, and the second aperture includes one or more apertures.

6. The carrier segment according to claim 1, wherein a longitudinal axis of the first aperture is substantially perpendicular or normal to the turbine casing.

7. The carrier segment according to claim 1, wherein the second impingement carrier wall extends between front and rear carrier ends and has an undulating circumferential profile.

8. The carrier segment according to claim 1, wherein air is exhausted from the third intermediate chamber and through the turbine casing with an exhaust valve.

9. The carrier segment according to claim 1, wherein a cooling chamber is disposed radially inwardly of the second impingement carrier wall.

10. The carrier segment according to claim 1, wherein the support includes one or more cut-out sections.

11. The carrier segment according to claim 8, wherein:

when the exhaust valve is in a closed position, air passes through the third aperture and contacts a radially inward surface of the turbine casing, and

when the exhaust valve is in an open position, air passes through the third aperture and through the turbine casing such that the air is radially outwardly of the turbine casing.

12. The carrier segment according to claim 11, wherein a fourth aperture is disposed between the first intermediate chamber and the third intermediate chamber for passage of air.

13. The carrier segment according to claim 12, wherein:

when the exhaust valve is in the closed position, air passes from the third intermediate chamber, through the fourth aperture, and into the first intermediate chamber, and

when the exhaust valve is in the open position, air passes from the first intermediate chamber, through the fourth aperture, and into the third intermediate chamber.

14. The carrier segment according to claim 1, wherein the support is located radially inwardly of the turbine casing and radially outwardly of the second intermediate chamber.

15. The carrier segment according to claim 9, further including another aperture that is configured to allow ingress of air from the first intermediate chamber to the cooling chamber.

16. A gas turbine engine comprising a carrier section according to claim 1.

17. The carrier segment according to claim 15, wherein the another aperture is located in a wall that borders the first intermediate chamber and the cooling chamber.

18. The carrier segment according to claim 1, wherein the third intermediate chamber includes an exhaust valve configured to control a direction of air flowing through the extension section aperture, and

wherein the air through the extension section aperture flows from the third intermediate chamber to the first intermediate chamber when the exhaust valve is closed and from the first intermediate chamber to the third intermediate chamber when the exhaust valve is open.