Metered orifice for motoring of a gas turbine engine

Patent metadata

Field	Value
Publication number	US-10823079-B2
Application number	US-201615363434-A
Country	US
Kind code	B2
Filing date	Nov 29, 2016
Priority date	Nov 29, 2016
Publication date	Nov 3, 2020
Grant date	Nov 3, 2020

Abstract

A system for motoring a gas turbine engine of an aircraft is provided. The system includes an air turbine starter operable to drive rotation of a starting spool of the gas turbine engine and a starter air valve operable to deliver compressed air to the air turbine starter in response to the starter air valve being open. The system also includes a metered orifice coupled in a bypass configuration around the starter air valve to deliver a reduced amount of the compressed air to the air turbine starter while the starter air valve is closed. The reduced amount of the compressed air delivered to the air turbine starter limits a motoring speed of the gas turbine engine below a resonance speed of the starting spool of the gas turbine engine.

First claim

What is claimed is:

1. A system for motoring a gas turbine engine of an aircraft, the system comprising:
an air turbine starter operable to drive rotation of a starting spool of the gas turbine engine;
a first duct coupled to a compressed air source;
a second duct coupled to the air turbine starter;
a starter air valve coupled to the first duct and the second duct, the starter air valve operable to receive compressed air from the compressed air source through the first duct and deliver the compressed air through the second duct to the air turbine starter in response to the starter air valve being open;
a metered orifice coupled to the first duct and the second duct in a bypass configuration around the starter air valve, the metered orifice sized to deliver a reduced amount of the compressed air from the first duct to the second duct and the air turbine starter while the starter air valve is closed; and
a controller configured to:
determine a motoring time to mitigate a bowed rotor condition of the gas turbine engine at a target speed set based on the reduced amount of the compressed air delivered through the metered orifice to the air turbine starter while the starter air valve is closed, wherein the reduced amount of the compressed air delivered to the air turbine starter limits a motoring speed of the gas turbine engine below a resonance speed of the starting spool of the gas turbine engine; and
initiate opening of the starter air valve after the motoring time expires to start the gas turbine engine.

2. The system as in claim 1 , wherein the compressed air source comprises an auxiliary power unit, a ground cart, or a cross engine bleed.

3. The system as in claim 1 , wherein the controller is operable to monitor one or more parameters comprising: an engine speed of the gas turbine engine, a starter speed of the air turbine starter, and a starter air pressure.

4. The system as in claim 3 , wherein the controller is operable to request an adjustment to the compressed air source based on the one or more parameters and/or adjust the motoring time based on the one or more parameters.

5. The system as is claim 1 , further comprising a variable valve in series with the metered orifice in the bypass configuration around the starter air valve to dynamically control the reduced amount of the compressed air delivered to the air turbine starter.

6. The system as in claim 1 , wherein a mitigation monitor determines whether bowed rotor mitigation was successful prior to allowing the motoring speed of the gas turbine engine to reach the resonance speed of the starting spool of the gas turbine engine.

7. A system of an aircraft, the system comprising:
an air turbine starter operable to drive rotation of a starting spool of a gas turbine engine of the aircraft in response to receiving compressed air;
a first duct coupled to a compressed air source;
a second duct coupled to the air turbine starter;
a starter air valve coupled to the first duct and the second duct, the starter air valve operable to deliver the compressed air through the second duct to the air turbine starter in response to the starter air valve being open;
a metered orifice coupled to the first duct and the second duct in a bypass configuration around the starter air valve, the metered orifice sized to deliver a reduced amount of the compressed air from the first duct to the second duct and the air turbine starter while the starter air valve is closed; and
a controller configured to:
determine a motoring time to mitigate a bowed rotor condition of the gas turbine engine at a target speed set based on the reduced amount of the compressed air delivered through the metered orifice to the air turbine starter while the starter air valve is closed, wherein the reduced amount of the compressed air delivered to the air turbine starter limits a motoring speed of the gas turbine engine below a resonance speed of the starting spool of the gas turbine engine; and
initiate opening of the starter air valve after the motoring time expires.

8. The system of claim 7 , wherein the controller is operable to monitor one or more parameters comprising: an engine speed of the gas turbine engine, a starter speed of the air turbine starter, and a starter air pressure.

9. The system of claim 8 , wherein the compressed air source comprises an auxiliary power unit and the controller is operable to request an adjustment to the auxiliary power unit based on the one or more parameters.

10. The system of claim 8 , wherein the compressed air source comprises an auxiliary power unit and the controller is operable to adjust the motoring time based on the one or more parameters and/or adjust a valve between the starter air valve and the auxiliary power unit based on the one or more parameters.

11. The system of claim 7 , further comprising a variable valve in series with the metered orifice in the bypass configuration around the starter air valve to dynamically control the reduced amount of the compressed air delivered to the air turbine starter based on one or more command signals from the controller.

12. The system of claim 7 , wherein a mitigation monitor determines whether bowed rotor mitigation was successful prior to allowing the motoring speed of the gas turbine engine to reach the resonance speed of the starting spool of the gas turbine engine.

13. A method for motoring of a gas turbine engine, the method comprising:
receiving compressed air from a compressed air source through a first duct coupled to the compressed air source and a starter air valve, the starter air valve controlling delivery of the compressed air from the first duct through a second duct to an air turbine starter;
delivering a reduced amount of the compressed air through a metered orifice coupled to the first duct and the second duct in a bypass configuration around the starter air valve to the air turbine starter while the starter air valve is closed;
determining, by a controller, a motoring time to mitigate a bowed rotor condition of the gas turbine engine at a target speed set based on the reduced amount of the compressed air delivered through the metered orifice to the air turbine starter while the starter air valve is closed, wherein the reduced amount of the compressed air delivered to the air turbine starter limits a motoring speed of the gas turbine engine below a resonance speed of a starting spool of the gas turbine engine; and
initiating opening of the starter air valve after the motoring time expires to start the gas turbine engine.

14. The method as in claim 13 , wherein the compressed air source comprises an auxiliary power unit, a ground cart, or a cross engine bleed.

15. The method as in claim 13 , further comprising monitoring one or more parameters comprising: an engine speed of the gas turbine engine, a starter speed of the air turbine starter, and a starter air pressure.

16. The method as in claim 15 , further comprising requesting an adjustment to the compressed air source based on the one or more parameters.

17. The method as in claim 15 , wherein the compressed air source comprises an auxiliary power unit and further comprising adjusting the motoring time based on the one or more parameters and/or adjusting a valve between the starter air valve and the auxiliary power unit based on the one or more parameters.

18. The method as in claim 13 , further comprising adjusting a variable valve in series with the metered orifice in the bypass configuration around the starter air valve to dynamically control the reduced amount of the compr

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Maalouf Fadi S
• Bintz Matthew E

Classifications

• B64D27/10

  of gas-turbine type  (jet aircraft B64D27/16) · CPC title

• B64D31/02

  Initiating means · CPC title

• F05D2270/304

  Spool rotational speed · CPC title

• F02C7/26

  Starting; Ignition · CPC title

• F05D2260/85

  Starting · CPC title