Gas turbine engine with transmission
AssigneePratt & Whitney Canada Corp.
InventorsJean DUBREUIL, Stephen KENNY
Life of this patent
Estimating the term…
Abstract
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.
Claims20
A gas turbine engine comprising:
- at least one turbine rotor drivingly engaged to an engine spool;
- a transmission having a first rotatable member coupled to the spool, a second rotatable member, and coupled rotatable members defining at least first and second alternate transmission paths between the first and second members, 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 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;
- and
- at least one compressor rotor coupled to the second member.
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 first rotatable member, a second rotatable member, and coupled rotatable members defining at least first and second 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;
- means for selecting any single one of the transmission paths, the means drivingly engaging the first and second members through the single one of the transmission paths;
- a low pressure shaft drivingly interconnecting each turbine rotor to the first member;
- and
- a 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.
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 defining a plurality of alternate discrete transmission ratios between rotational speeds of the compressor rotor and the power shaft;
- and
- adjusting the transmission to a selected one of the transmission ratios.
Dependencies are inferred from the claim text.