ROTOR BLADE TIP CLEARANCE CONTROL

• US 20110229306A1
• Filed: 03/17/2011
• Published: 09/22/2011
• Est. Priority Date: 03/17/2010
• Status: Active Grant

• Current Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Inventors: LEWIS, Leo V., BACIC, Marko
• Granted Patent: US 8,721,257 B2
• Time in Patent Office: Days
• US Class Current: 415/115
• CPC Class Codes: F01D 11/24 by selectively cooling-heating stator or rotor components
• CPC Class Codes: F05D 2240/11 Shroud seal segments
• CPC Class Codes: F05D 2260/201 by impingement of a fluid
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A gas turbine engine has a row of circumferentially spaced rotor blades and a plurality of seal segments circumscribing the rotor blade tips and attached to a radially inward side of a casing of the engine. The seal segments are spaced from the casing by a spacing cavity. A flow of relatively hot cooling air is routed to the spacing cavity to cool the seal segments. The engine has an external cooling arrangement for impinging relatively cold cooling air on a radially outward side of the casing. The engine has a wall containing a plurality of through-holes which is attached to a radially inward side of the casing adjacent the seal segments. The wall is spaced from the casing to define a heating control chamber between the wall and the casing. The engine has one or more closable ducts which allow air to be exhausted from the heating control chamber.

Claims

1. A gas turbine engine having:

a row of circumferentially spaced rotor blades, each having a radially outer tip,

a plurality of seal segments circumscribing the rotor blade tips and attached to a radially inward side of a casing of the engine, the seal segments being spaced from the casing by a spacing cavity, whereby, in use, a flow of relatively hot cooling air is routed to the spacing cavity to provide cooling for the seal segments, and

an external cooling arrangement for impinging relatively cold cooling air on a radially outward side of the casing and thereby controlling a radial clearance between the rotor blade tips and the seal segments;

wherein the engine further has a wall containing a plurality of through-holes which is attached to a radially inward side of the casing adjacent the seal segments, the wall being spaced from the casing to define a heating control chamber between the wall and the casing, and the engine further has one or more closable ducts which allow air to be exhausted from the heating control chamber, whereby, when the ducts are open, a portion of the hot cooling air flows through the through-holes to impinge on the casing and then exhausts from the heating control chamber through the ducts.

2. A gas turbine engine according to claim 1, wherein the wall is a dividing wall which separates the spacing cavity into two radially spaced chambers, the radially inner sub-chamber receiving the flow of hot cooling air, and the radially outer sub-chamber being the heating control chamber.

3. A gas turbine engine according to claim 2, wherein the engine further has a second wall containing a plurality of through-holes which is attached to a radially inward side of the casing adjacent the seal segments, the second wall being spaced from the casing to define a second heating control chamber between the wall and the casing, the second wall and the second heating control chamber being located forward of the spacing cavity;

wherein the engine further has one or more second closable ducts which allow air to be exhausted from the second heating control chamber, whereby, when the second ducts are open, a portion of the hot cooling air flows through the through-holes of the second wall to impinge on the casing and then exhausts from the second heating control chamber through the second ducts.

4. A gas turbine engine according to claim 1, wherein the wall and the heating control chamber are located forward of the spacing cavity.

5. A gas turbine engine according to claim 1, wherein the ducts exhaust the hot cooling air to the radially inward side of the casing.

6. A gas turbine engine according to claim 5, wherein

the wall and the heating control chamber are located forward of the spacing cavity, and

the ducts exhaust the hot cooling air into the spacing cavity.

7. A gas turbine engine according to claim 1, wherein the ducts exhaust the hot cooling air to the radially outward side of the casing.

8. A gas turbine engine according to claim 1, wherein the cooling arrangement is configured such that the amount of impinging cold cooling air can be controllably varied.

9. A gas turbine engine according to claim 1, wherein the cooling arrangement comprises a manifold circumscribing the casing, the manifold carrying the cold cooling air and having a plurality of further through-holes at a radially inner side thereof through which the cold cooling air flows to impinge on the casing.

10. A gas turbine engine according to claim 9, wherein

the ducts exhaust the hot cooling air to the radially outward side of the casing, and

the ducts exhaust the hot cooling air into the manifold.

11. A gas turbine engine according to claim 1, further having a computer-based control system for controlling the flow of hot cooling air through the ducts, the cooling system being arranged such that the ducts open when the engine accelerates from a cruise operating condition.

12. A gas turbine engine according to claim 11, wherein

the cooling arrangement is configured such that the amount of impinging cold cooling air can be controllably varied, and

the computer-based control system further controls the impingement of cold cooling air on the casing from the cooling arrangement, the cooling system being further arranged such that, when the ducts are open, the impingement of cold cooling air on the casing from the cooling arrangement is reduced or prevented.

13. The computer-based control system of claim 11.

14. A method of operating the gas turbine engine of claim 1, the method comprising the steps of:

(a) running the engine at a cruise operating condition with the ducts closed, and

(b) accelerating the engine and opening the ducts so that hot cooling air flows through the through-holes to impinge on the casing.

15. A method according to claim 14, wherein, during step (a), cold cooling air from the external cooling arrangement impinges on the radially outward side of the casing.

16. A method according to claim 15, wherein, during step (b), the impingement of cold cooling air from the external cooling arrangement on the radially outward side of the casing is reduced or prevented.

17. A method according to claim 14, further comprising the steps, after step (b), of:

(c) closing the ducts, and

(d) running the engine at a second cruise operating condition.

18. A method according to claim 17, wherein,

during step (b), the impingement of cold cooling air from the external cooling arrangement on the radially outward side of the casing is reduced or prevented, and

after step (b), impingement of cold cooling air from the external cooling arrangement on the radially outward side of the casing is increased or recommenced.