METERED ORIFICE FOR MOTORING OF A GAS TURBINE ENGINE
First Claim
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 starter air valve operable to deliver compressed air to the air turbine starter in response to the starter air valve being open; and
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, 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.
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Accused Products
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.
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Citations
20 Claims
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1. A system for motoring a gas turbine engine of an aircraft, the system comprising:
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an air turbine starter operable to drive rotation of a starting spool of the gas turbine engine; a starter air valve operable to deliver compressed air to the air turbine starter in response to the starter air valve being open; and 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, 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. - View Dependent Claims (2, 3, 4, 5, 6, 7)
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8. A system of an aircraft, the system comprising:
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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 starter air valve operable to deliver the compressed air to the air turbine starter in response to the starter air valve being open; 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, 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 a controller operable to determine a motoring time to mitigate a bowed rotor condition of the gas turbine engine and initiate opening of the starter air valve after the motoring time expires. - View Dependent Claims (9, 10, 11, 12, 13)
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14. A method for motoring of a gas turbine engine, the method comprising:
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determining, by a controller, a motoring time to mitigate a bowed rotor condition of the gas turbine engine; delivering a reduced amount of compressed air through a metered orifice coupled in a bypass configuration around a starter air valve to an air turbine starter that 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. - View Dependent Claims (15, 16, 17, 18, 19, 20)
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Specification