Speed control during motoring of a gas turbine engine
First Claim
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1. A system for speed control during motoring of a first gas turbine engine of an aircraft comprising at least two gas turbine engines, the system comprising:
- an air turbine starter;
a starter air valve operable to deliver compressed air to the air turbine starter; and
a controller operable to adjust the starter air valve to control motoring of the first gas turbine engine based on measured feedback with lead compensation providing a phase lead with a positive phase angle frequency response to reject disturbances attributable to dual to single or single to dual engine starting transitions between the at least two gas turbine engines.
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Abstract
A system is provided for speed control during motoring of a gas turbine engine of an aircraft. The system includes an air turbine starter, a starter air valve operable to deliver compressed air to the air turbine starter, and a controller. The controller is operable to adjust the starter air valve to control motoring of the gas turbine engine based on measured feedback with lead compensation to reject disturbances attributable to dual to single or single to dual engine starting transitions.
114 Citations
20 Claims
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1. A system for speed control during motoring of a first gas turbine engine of an aircraft comprising at least two gas turbine engines, the system comprising:
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an air turbine starter; a starter air valve operable to deliver compressed air to the air turbine starter; and a controller operable to adjust the starter air valve to control motoring of the first gas turbine engine based on measured feedback with lead compensation providing a phase lead with a positive phase angle frequency response to reject disturbances attributable to dual to single or single to dual engine starting transitions between the at least two gas turbine engines. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8)
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9. 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 first gas turbine engine of the aircraft in response to compressed air received from a compressed air source, wherein the aircraft comprises at least two gas turbine engines; a starter air valve operable to deliver the compressed air to the air turbine starter; and a controller operable to adjust the starter air valve to control motoring of the gas turbine engine based on measured feedback with lead compensation providing a phase lead with a positive phase angle frequency response to reject disturbances attributable to dual to single or single to dual engine starting transitions between the at least two gas turbine engines. - View Dependent Claims (10, 11, 12, 13, 14)
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15. A method for speed control during motoring of a first gas turbine engine of an aircraft comprising at least two gas turbine engines, the method comprising:
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commanding, by a controller, a starter air valve to control delivery of compressed air to an air turbine starter during motoring of the first gas turbine engine; and adjusting the starter air valve based on measured feedback with lead compensation providing a phase lead with a positive phase angle frequency response to reject disturbances attributable to dual to single or single to dual engine starting transitions between the at least two gas turbine engines. - View Dependent Claims (16, 17, 18, 19, 20)
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Specification