초록 ▼

A gas turbine engine with a transmission having a first rotatable member coupled to an engine spool, a second rotatable member coupled to a compressor rotor, and coupled rotatable members defining at least first and second alternate transmission paths between the first and second members. Each trans

A gas turbine engine with a transmission having a first rotatable member coupled to an engine spool, a second rotatable member coupled to a compressor rotor, and coupled rotatable members defining at least first and second alternate transmission paths between the first and second members. Each transmission path defines a different fixed transmission ratio of a rotational speed of the second member on a rotational speed of the first member.

대표청구항 ▼

1. A gas turbine engine comprising: at least one turbine rotor drivingly engaged to an engine spool;a transmission having a rotatable first member coupled to the spool, a rotatable second member, and rotatable coupled members defining at least first and second alternate transmission paths between th

1. A gas turbine engine comprising: at least one turbine rotor drivingly engaged to an engine spool;a transmission having a rotatable first member coupled to the spool, a rotatable second member, and rotatable coupled members defining at least first and second alternate transmission paths between the first and second members, each transmission path being defined by the coupled members of the respective one of the transmission paths and defining a different fixed transmission ratio of a rotational speed of the second member on a rotational speed of the first member;an actuation mechanism having at least first and second positions, the actuation mechanism in each position drivingly engaging the first and second members to the coupled members of a single respective one of the transmission paths, the actuation mechanism in each position including at least one brake removably engaged with and preventing rotation of one of the coupled members of the respective one of the transmission paths; andat least one compressor rotor coupled to the second member. 2. The gas turbine engine as defined in claim 1, wherein the second member is also coupled to one element selected from the group consisting of a fan, a propeller, and an output shaft of the engine. 3. The gas turbine engine as defined in claim 1, wherein the coupled members include at least one common member between the first and second transmission paths, at least one respective upstream member for each of the first and second transmission paths upstream of the at least one common member and at least one respective downstream member for each of the first and second transmission paths downstream of the at least one common member, the coupled members defining a third alternate transmission path with the at least one respective upstream member of the first transmission path, the at least one common member and the at least one respective downstream member of the second transmission path, and a fourth transmission path with the at least one respective upstream member of the second transmission path, the at least one common member and the at least one respective downstream member of the first transmission path, the actuation mechanism further having third and fourth positions respectively corresponding to the third and fourth transmission paths. 4. The gas turbine engine as defined in claim 1, wherein the first member is a first carrier and the second member is a second carrier, the coupled members including at least first, second and third sets of planetary gears supported by one of the first and second carriers and fourth and fifth sets of planetary gears supported by the other of the first and second carrier, the third and fourth sets of planetary gears being drivingly engaged to one another through at least one of the coupled members, the coupled members further including a respective sun gear coupled to each one of the first, second and fifth sets of planetary gears, the actuation mechanism in the first position preventing rotation of the sun gears coupled to first and fifth sets of planetary gears while allowing the sun gear coupled to the second set of planetary gears to rotate freely, and in the second position preventing rotation of the sun gears coupled to second and fifth sets of planetary gears while allowing the sun gear coupled to the first set of planetary gears to rotate freely. 5. The gas turbine engine as defined in claim 4, wherein the third and fourth sets of planetary gears are each coupled to a respective one of two interconnected sun gears. 6. The gas turbine engine as defined in claim 4, wherein the coupled members further includes a sixth set of planetary gears supported by the other of the first and second carriers and the coupled members further include a sun gear coupled to the sixth set of planetary gears, the actuation mechanism in the first and second positions allowing the sun gear coupled to the sixth set of planetary gears to rotate freely, in a third position preventing rotation of the sun gears coupled to first and sixth sets of planetary gears while allowing the sun gear coupled to the second and fifth sets of planetary gears to rotate freely, and in a fourth position preventing rotation of the sun gears coupled to second and sixth sets of planetary gears while allowing the sun gear coupled to the first and fifth sets of planetary gears to rotate freely. 7. The gas turbine engine as defined in claim 4, wherein the at least one brake of the actuation mechanism includes a respective brake selectively engageable with the sun gear coupled to each one of the first, second and fifth sets of planetary gears. 8. The gas turbine engine as defined in claim 6, wherein the at least one brake of the actuation mechanism includes a respective brake selectively engageable with the sun gear coupled to each one of the first, second, fifth and sixth sets of planetary gears. 9. The gas turbine engine as defined in claim 1, wherein the transmission ratios of the rotational speed of the second member on the rotational speed of the first member include at least one ratio having a value of at least 1 and at least one ratio having a value lower than 1. 10. A gas turbine engine comprising: a low pressure turbine located downstream of and in fluid communication with an exhaust of a high pressure section of the engine, the low pressure turbine having at least one turbine rotor;a transmission having a rotatable first member, a rotatable second member, and rotatable coupled members defining at least first, second, third and fourth alternate transmission paths, each transmission path defining a different fixed transmission ratio of a rotational speed of the second member on a rotational speed of the first member;an actuation mechanism having at least first, second, third and fourth positions, the actuation mechanism in each position drivingly engaging the first and second members through a single respective one of the transmission paths;a low pressure shaft drivingly interconnecting each turbine rotor to the first member; anda low pressure compressor located upstream of and having an exhaust in fluid communication with the high pressure section of the engine, the low pressure compressor having at least one compressor rotor drivingly interconnected to the second member. 11. The gas turbine engine as defined in claim 10, wherein each transmission path is defined by the coupled members of the respective one of the transmission paths and the actuation mechanism includes at least one brake removably engagable with a corresponding one of the coupled members in each one of the transmission paths. 12. The gas turbine engine as defined in claim 10, wherein the first member is a first carrier and the second member is a second carrier, the coupled members including at least first, second and third sets of planetary gears supported by one of the first and second carriers and fourth and fifth sets of planetary gears supported by the other of the first and second carrier, the third and fourth sets of planetary gears being drivingly engaged to one another through at least one of the coupled members, the coupled members further including a respective sun gear coupled to each one of the first, second and fifth sets of planetary gears, the actuation mechanism preventing rotation of the sun gears coupled to first and fifth sets of planetary gears while allowing the sun gear coupled to the second set of planetary gears to rotate freely for the first transmission path, and preventing rotation of the sun gears coupled to second and fifth sets of planetary gears while allowing the sun gear coupled to the first set of planetary gears to rotate freely for the second transmission path. 13. The gas turbine engine as defined in claim 12, wherein the third and fourth sets of planetary gears are each coupled to a respective one of two interconnected sun gears. 14. The gas turbine engine as defined in claim 12, wherein the coupled members further includes a sixth set of planetary gears supported by the other of the first and second carriers and the coupled members further include a sun gear coupled to the sixth set of planetary gears, the actuation mechanism allowing the sun gear coupled to the sixth set of planetary gears to rotate freely for the first and second transmission paths, preventing rotation of the sun gears coupled to first and sixth sets of planetary gears while allowing the sun gear coupled to the second and fifth sets of planetary gears to rotate freely for a third transmission path, and preventing rotation of the sun gears coupled to second and sixth sets of planetary gears while allowing the sun gear coupled to the first and fifth sets of planetary gears to rotate freely for a fourth transmission path. 15. The gas turbine engine as defined in claim 10, wherein the transmission ratios of the rotational speed of the second member on the rotational speed of the first member include at least one ratio having a value of at least 1 and at least one ratio having a value lower than 1. 16. A method of adjusting a rotational speed of a compressor rotor of a gas turbine engine, the method comprising: keeping a rotational speed of interconnected compressor and turbine rotors of a high pressure section of the engine at a constant value;rotating at least one rotor of a low pressure turbine with a flow of exhaust gases from the high pressure section;driving a rotation of the compressor rotor with a power shaft driven by the at least one rotor of the low pressure turbine through a transmission having a plurality of transmission paths defining a plurality of alternate discrete transmission ratios between rotational speeds of the compressor rotor and the power shaft; andadjusting the transmission to a selected one of the transmission ratios, including actuating a selected one of the plurality of transmission paths by preventing a rotation of at least one rotatable member in the selected one of the transmission paths and allowing a free rotation of at least one rotatable member in each one but the selected one of the plurality of transmission paths. 17. The method as defined in claim 16, further including driving a rotation of one element selected from the group consisting of a fan, a propeller, and an output shaft of the engine through the transmission.