Active turbine tip clearance control system

Patent metadata

Field	Value
Publication number	US-9316111-B2
Application number	US-201113326434-A
Country	US
Kind code	B2
Filing date	Dec 15, 2011
Priority date	Dec 15, 2011
Publication date	Apr 19, 2016
Grant date	Apr 19, 2016

Abstract

An active tip clearance control (ATCC) system of a gas turbine engine includes an ejector to selectively drive an air flow passing through the ATCC system. A high pressure air flow as a motive flow of the ejector is controlled by a valve according to engine operation requirements.

First claim

The invention claimed is:

1. An active tip clearance control (ATCC) system of a gas turbine engine comprising an ATCC manifold disposed adjacent a rotor case, the manifold configured for directing air over the rotor case, an inlet passage fluidly connecting the ATCC manifold with an air source selected from one of ambient air and a fan driven bypass air flow directed through a bypass duct of the engine, a vent passage in fluid communication with the manifold and the atmosphere for venting air received from the ATCC manifold to the atmosphere, a controllable valve receiving and controlling a compressor air flow, and an ejector for ejecting the controlled compressor air flow to selectively drive only said selected one of ambient air and fan driven bypass air flow through the ATCC manifold.

2. The active tip clearance control (ATCC) system as defined in claim 1 wherein the ejector is mounted on the inlet passage and positioned upstream of the manifold to drive the air through the inlet passage towards the ATCC manifold.

3. The active tip clearance control (ATCC) system as defined in claim 1 wherein the ejector is mounted on the vent passage and positioned downstream of the manifold to drive the air through the vent passage and away from the ATCC manifold.

4. The active tip clearance control (ATCC) system as defined in claim 1 wherein the vent passage is in fluid communication with the atmosphere via the bypass duct.

5. An aircraft turbofan gas turbine engine comprising:
an annular outer case surrounding a fan assembly;
an annular core case positioned within the outer case and accommodating a compressor assembly, a combustion gas generator assembly and a turbine assembly, the annular outer and core cases defining an annular bypass duct therebetween for directing a bypass air flow driven by the fan assembly to pass therethrough; and
an active tip clearance control (ATCC) apparatus including an ATCC manifold mounted to a turbine case for discharging cooling air over the turbine case to cool the same, an inlet passage connecting the ATCC manifold with the bypass duct at a first location of the bypass duct, a vent passage disposed downstream of the ATCC manifold and being in fluid communication with the bypass duct at a second location of the bypass duct downstream of the first location, the ATCC apparatus further including a solenoid valve controlling a compressor air flow and an ejector for ejecting the controlled compressor air to selectively drive only the bypass air flow as the cooling air through the ATCC manifold.

6. The aircraft turbofan gas turbine engine as defined in claim 5 wherein the ejector is mounted on the inlet passage to drive the cooling air through the inlet passage towards the ATCC manifold.

7. The aircraft turbofan gas turbine engine as defined in claim 5 wherein the ejector is mounted on the vent passage to drive the cooling air through the vent passage and away from the ATCC manifold.

8. The aircraft turbofan gas turbine engine as defined in claim 5 wherein the ejector is formed with a hole defined in a side wall of one of the inlet and vent passages for receiving the controlled compressor air flow to be injected into said one of the inlet and vent passages.

9. The aircraft turbofan gas turbine engine as defined in claim 5 wherein a volume of the compressor air flow is smaller than a volume of the cooling air flow in each time unit.

10. A method for controlling an active tip clearance control (ATCC) system to cool a turbine casing of a gas turbine engine, comprising amplifying a control signal for actuating the ATCC system in steps of:
a) electively actuating a solenoid valve using an electric signal as the control signal to control an on/off condition of a compressor air flow; and
b) using the on/off-controlled compressor air flow to selectively actuate an ejector which drives a cooling air flow introduced only from a bypass duct of the engine through the ATCC system and vented to the bypass duct, thereby selectively increasing an energy level of the cooling air flow passing through the ATCC system, resulting in an increased pressure differential over the ATCC system.

11. The method as defined in claim 10 wherein a volume of the compressor air flow is smaller than a volume of the cooling air flow in each time unit.

12. The method as defined in claim 10 wherein in step (b) the compressor air flow is injected by the ejector into the cooling air flow in the ATCC system upstream of the turbine casing which the ATCC system selectively discharges the cooling air flow to cool, thereby boosting the cooling air flow upstream of the turbine case to a high pressure level.

13. The method as defined in claim 10 wherein in step (b) the compressor air flow is injected by the ejector into the cooling air flow in the ATCC system, downstream of the turbine casing which the ATCC system selectively discharges the cooling air flow to cool, thereby increasing a momentum of the cooling air flow downstream of the turbine case in order to create a suction effect on the cooling air flow discharged from the ATCC system.

Assignees

• Eleftheriou Andreas
• Alecu Daniel
• Pratt & Whitney Canada

Inventors

• Eleftheriou Andreas
• Alecu Daniel

Classifications

• F01D11/22

  by mechanically actuating the stator or rotor components, e.g. moving shroud sections relative to the rotor · CPC title

• F01D11/24 Primary

  by selectively cooling-heating stator or rotor components · CPC title

• F01D11/20 Primary

  Actively adjusting tip-clearance · CPC title