Method, system, and apparatus for reducing a turbine clearance

• US 9,758,252 B2
• Filed: 03/22/2016
• Issued: 09/12/2017
• Est. Priority Date: 08/23/2012
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Adibhatla, Sridhar, Nolte, Steven Edward, Moeller, Gerhard Walter, Gallagher, Christopher Timothy, Hanify, John William, Ingram, Grant Alan
• Primary Examiner(s): Edwards, Jerrah
• Assistant Examiner(s): Williams, Kelly D
• Application Number:
  US15/077,731
• Publication Number:
  US 20160311546A1
• Time in Patent Office: 539 Days
• CPC Class Codes: B64D 31/06 actuated automatically
• CPC Class Codes: F01D 11/24 by selectively cooling-heating stator or rotor components

Abstract

A method for reducing a turbine clearance gap between a plurality of rotor blades of a turbine engine and a shroud of the turbine engine is provided. The method includes determining that an airplane is in a first flight condition, and adjusting the turbine clearance gap to a first clearance gap distance associated with the first flight condition. The method also includes determining a demand for a second flight condition, and adjusting an engine responsiveness to a first engine responsiveness for a first predetermined change in a power parameter of the engine. The method further includes reducing the engine responsiveness from the first engine responsiveness level to a second engine responsiveness level for a second predetermined change in the power parameter of the engine, and closing a clearance control valve associated with the shroud during the second predetermined change in the power parameter of the engine.

Claims

1. A method for reducing a turbine clearance gap between a plurality of rotor blades of a turbine engine and a shroud of the turbine engine, said method comprising:

determining, with a flight operation controller, that an airplane is in a first flight condition;

adjusting the turbine clearance gap to a first clearance gap distance associated with the first flight condition;

determining, with the flight operation controller, a demand for a second flight condition;

adjusting an engine responsiveness to a first engine responsiveness level for a first predetermined change in a power parameter of the turbine engine;

wherein the power parameter includes fan speed, and wherein adjusting an engine responsiveness to a first engine responsiveness level for a first predetermined change in a power parameter of the engine comprises adjusting the engine responsiveness to the first engine responsiveness level for a first predetermined change in fan speed over a first predetermined change in power level;

reducing the engine responsiveness from the first engine responsiveness level to a second engine responsiveness level for a second predetermined change in the power parameter of the turbine engine; and

closing a clearance control valve associated with the shroud during the second predetermined change in the power parameter of the turbine engine.

2. The method in accordance with claim 1, reducing the engine responsiveness from the first engine responsiveness level to a second engine responsiveness level for a second predetermined change in the power parameter of the engine comprises reducing the engine responsiveness to the second engine responsiveness level for a second predetermined change in fan speed over a second predetermined change in power level greater than the first predetermined change in power level.

3. The method in accordance with claim 1, wherein closing a clearance control valve associated with the shroud during the second predetermined change in the power parameter of the engine comprises closing one or more clearance control valves in flow communication with the shroud.

4. The method in accordance with claim 1, wherein determining that an airplane is in a first flight condition includes determining that the airplane is in a steady-state cruise condition.

5. The method in accordance with claim 1, wherein reducing the engine responsiveness from the first engine responsiveness level to a second engine responsiveness level for a second predetermined change in the power parameter of the engine comprises limiting engine acceleration in response to a throttle increase.

6. A clearance control system for reducing a turbine clearance gap between a plurality of blades of a turbine engine and a shroud of the turbine engine, said clearance control system comprising a flight operation controller configured to:

determine that an airplane is in a first flight condition;

adjust the turbine clearance gap to a first clearance gap distance associated with the first flight condition;

determine a demand for a second flight condition;

adjust an engine responsiveness to a first engine responsiveness level for a first predetermined change in a power parameter of the turbine engine;

wherein the power parameter includes fan speed, and wherein the flight operation controller is further configured to adjust the engine responsiveness to the first engine responsiveness level for a first predetermined change in fan speed over a first predetermined change in power level

reduce the engine responsiveness from the first engine responsiveness level to a second engine responsiveness level for a second predetermined change in the power parameter of the turbine engine; and

close a clearance control valve associated with the shroud during the second predetermined change in the power parameter of the turbine engine.

7. The clearance control system in accordance with claim 6, wherein the flight operation controller is further configured to reduce the engine responsiveness to the second engine responsiveness level for a second predetermined change in fan speed over a second predetermined change in power level greater than the first predetermined change in power level.

8. The clearance control system in accordance with claim 6, wherein the flight operation controller is further configured to close one or more clearance control valves in flow communication with the shroud.

9. The clearance control system in accordance with claim 6, wherein the first flight condition is a steady-state cruise condition.

10. The clearance control system in accordance with claim 6, wherein the second engine responsiveness level limits engine acceleration in response to a throttle increase.

11. An airplane comprising:

a plurality of turbine engines; and

a clearance control system for reducing a turbine clearance gap between a plurality of blades and a shroud of at least one of the plurality of turbine engines, the clearance control system comprising a flight operation controller configured to;

determine that the airplane is in a first flight condition;

adjust the turbine clearance gap to a first clearance gap distance associated with the first flight condition;

determine a demand for a second flight condition;

adjust an engine responsiveness to a first engine responsiveness level for a first predetermined change in a power parameter of the at least one of the plurality of turbine engines;

wherein the power parameter includes fan speed, and wherein the flight operation controller is further configured to adjust the engine responsiveness to the first engine responsiveness level for a first predetermined change in fan speed over a first predetermined change in power level;

reduce the engine responsiveness from the first engine responsiveness level to a second engine responsiveness level for a second predetermined change in the power parameter of the at least one of the plurality of turbine engines; and

close a clearance control valve associated with the shroud during the second predetermined change in the power parameter of the at least one of the plurality of turbine engines.

12. The airplane in accordance with claim 11, wherein the flight operation controller is further configured to reduce the engine responsiveness to the second engine responsiveness level for a second predetermined change in fan speed over a second predetermined change in power level greater than the first predetermined change in power level.

13. The airplane in accordance with claim 11, wherein the flight operation controller is further configured to close one or more clearance control valves in flow communication with the shroud.

14. The airplane in accordance with claim 11, wherein the first flight condition is a steady-state cruise condition.