OPERATION OF AIRCRAFT ENGINES DURING TRANSIENT CONDITIONS
First Claim
1. A method for operating an aircraft engine during a transient condition of the aircraft engine, the aircraft engine including a turbine having at least a high-pressure turbine spool and a low-pressure turbine spool, the method comprising:
- identifying a transient condition of the aircraft engine during operation of the aircraft engine requiring one of an increase or decrease in rotational speed of the high-pressure spool;
conditioned upon the transient condition requiring an increase in rotational speed of the high-pressure spool, providing power from a source of power separate from the aircraft engine to the high-pressure spool to at least partially accelerate the high-pressure spool during the transient condition, the source of power comprising an electrical system of an aircraft; and
conditioned upon the transient condition requiring a decrease in rotational speed of the high-pressure spool, drawing power from the high-pressure spool to the electrical system to at least partially decelerate the high-pressure spool during the transient condition.
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Accused Products
Abstract
Aircraft engines and methods for operating such aircraft engines during transient conditions are described. An exemplary method comprises identifying a transient condition of the aircraft engine and at least partially absorbing the transient condition using an electrical system of the aircraft. When the transient condition requires acceleration of the engine, absorbing the transient condition may comprise transferring power from the electrical system to the high-pressure spool of the engine. When the transient condition requires deceleration of the engine, absorbing the transient condition may comprise transferring power from the high-pressure spool to the electrical system.
34 Citations
20 Claims
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1. A method for operating an aircraft engine during a transient condition of the aircraft engine, the aircraft engine including a turbine having at least a high-pressure turbine spool and a low-pressure turbine spool, the method comprising:
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identifying a transient condition of the aircraft engine during operation of the aircraft engine requiring one of an increase or decrease in rotational speed of the high-pressure spool; conditioned upon the transient condition requiring an increase in rotational speed of the high-pressure spool, providing power from a source of power separate from the aircraft engine to the high-pressure spool to at least partially accelerate the high-pressure spool during the transient condition, the source of power comprising an electrical system of an aircraft; and conditioned upon the transient condition requiring a decrease in rotational speed of the high-pressure spool, drawing power from the high-pressure spool to the electrical system to at least partially decelerate the high-pressure spool during the transient condition. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9)
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10. An aircraft engine comprising:
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a high-pressure spool; a low-pressure spool configured for rotation separate from the high-pressure spool; a controller configured to, during operation of the aircraft engine, identify a transient condition of the aircraft engine and command; conditioned upon the transient condition requiring an increase in rotational speed of the high-pressure spool, injection of power into the aircraft engine by transferring power from a source of power separate from the aircraft engine to the high-pressure spool to at least assist in achieving the required increase in rotational speed of the high-pressure spool during the transient condition, the source of power comprising an electrical system of an aircraft; and conditioned upon the transient condition requiring a decrease in rotational speed of the high-pressure spool, drawing of power from the aircraft engine by transferring power from the high-pressure spool to the electrical system to at least assist in achieving the required decrease in rotational speed of the high-pressure spool during the transient condition. - View Dependent Claims (11, 12, 13)
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14. A method for operating an aircraft engine during a transient condition of the aircraft engine, the aircraft engine comprising a gas turbine having a high-pressure spool and a low-pressure spool, the method comprising:
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identifying a transient condition of the aircraft engine during operation of the aircraft engine; and at least partially absorbing the transient condition of the aircraft engine using an electrical system of an aircraft by one of; injecting power into the aircraft engine by transferring power from the electrical system to the high-pressure spool; and drawing power from the aircraft engine by transferring power from the high-pressure spool to the electrical system. - View Dependent Claims (15, 16, 17, 18, 19, 20)
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Specification