GAS TURBINE ENGINE WITH TRANSMISSION AND METHOD OF ADJUSTING ROTATIONAL SPEED
First Claim
1. A method of adjusting a rotational speed of at least one low pressure compressor rotor of a gas turbine engine having independently rotatable low pressure and high pressure spools, the method comprising:
- rotating at least one rotor of a high pressure compressor of a core section of the engine with at least one rotor of a high pressure turbine of the core section through the high pressure spool;
rotating at least one rotor of a low pressure turbine with a flow of exhaust gases from the high pressure turbine section;
rotating the low pressure spool with the at least one rotor of the low pressure turbine;
rotating a load of the engine with the low pressure spool;
driving a rotation of the at least one low pressure compressor rotor with the low pressure spool through a variable transmission defining a variable transmission ratio between rotational speeds of the at least one compressor rotor and of the low pressure spool; and
adjusting the transmission ratio to obtain a desired rotational speed for the low pressure compressor rotor.
1 Assignment
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Accused Products
Abstract
A method of adjusting a rotational speed of the low pressure compressor rotor(s) of a gas turbine engine, including rotating the high pressure compressor rotor(s) with the high pressure turbine rotor(s) through the high pressure spool, rotating the low pressure turbine rotor(s) with a flow of exhaust gases from the high pressure turbine, rotating the low pressure spool with the low pressure turbine rotor(s), rotating a load of the engine with the low pressure spool, driving a rotation of the low pressure compressor rotor(s) with the low pressure spool through a variable transmission defining a variable transmission ratio between rotational speeds of the compressor rotor(s) and the low pressure spool, and adjusting the transmission ratio to obtain a desired rotational speed for the low pressure compressor rotor(s). A method of adjusting rotational speeds of a gas turbine engine and a gas turbine engine are also described.
156 Citations
20 Claims
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1. A method of adjusting a rotational speed of at least one low pressure compressor rotor of a gas turbine engine having independently rotatable low pressure and high pressure spools, the method comprising:
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rotating at least one rotor of a high pressure compressor of a core section of the engine with at least one rotor of a high pressure turbine of the core section through the high pressure spool; rotating at least one rotor of a low pressure turbine with a flow of exhaust gases from the high pressure turbine section; rotating the low pressure spool with the at least one rotor of the low pressure turbine; rotating a load of the engine with the low pressure spool; driving a rotation of the at least one low pressure compressor rotor with the low pressure spool through a variable transmission defining a variable transmission ratio between rotational speeds of the at least one compressor rotor and of the low pressure spool; and adjusting the transmission ratio to obtain a desired rotational speed for the low pressure compressor rotor. - View Dependent Claims (2, 3, 4, 5, 6)
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7. A method of adjusting rotational speeds of a gas turbine engine having independently rotatable low pressure and high pressure spools, the method comprising:
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selecting a first rotational speed for at least one high pressure compressor rotor and at least one high pressure turbine rotor of a core of the gas turbine engine; rotating the at least one high pressure compressor rotor with the at least one high pressure turbine rotor through the high pressure spool at the first rotational speed, a ratio between the first rotational speed and a rotational speed of the high pressure spool having a fixed value; selecting a second rotational speed for a load of the engine; selecting a third rotational speed for at least one low pressure compressor rotor of the engine; and adjusting a variable ratio of a transmission drivingly interconnecting the low pressure spool and the at least one low pressure compressor rotor to rotate the at least one low pressure compressor rotor at the third rotational speed while rotating the load at the second rotational speed with at least one low pressure turbine rotor of the engine through the low pressure spool, a ratio between the second rotational speed and a rotational speed of the low pressure spool having a fixed value. - View Dependent Claims (8, 9, 10, 11, 12, 13, 14)
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15. A gas turbine engine comprising:
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a core engine having at least one high pressure turbine rotor and at least one high pressure compressor rotor connected to a rotatable high pressure spool such as to be in driving engagement therewith with a fixed rotational speed ratio being defined therebetween; a low pressure spool rotatable independently of the high pressure spool; at least one low pressure turbine rotor connected to the low pressure spool such as to be in driving engagement therewith with a fixed rotational speed ratio being defined therebetween, the at least one low pressure turbine rotor extending in a flowpath in fluid communication with a flowpath receiving the at least one high pressure turbine rotor; a rotatable load in driving engagement with the low pressure spool; and a low pressure compressor rotor extending in a flowpath in fluid communication with a flowpath receiving the at least one high pressure compressor rotor, the low pressure compressor rotor being in driving engagement with the low pressure spool through a variable transmission defining a variable rotational speed ratio therebetween. - View Dependent Claims (16, 17, 18, 19, 20)
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Specification