Aircraft engine having two radially offset turbines
AssigneePratt & Whitney Canada Corp.
InventorDavid Menheere
Life of this patent
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Abstract
An aircraft engine, has: a high-pressure spool having a high-pressure turbine drivingly engaged to a high-pressure compressor; and a low-pressure spool having: a first low-pressure turbine downstream of the high-pressure turbine; and a second low-pressure turbine downstream of the first low-pressure turbine, one or more of the first low-pressure turbine and the second low-pressure turbine drivingly engaged to a rotatable load, the first low-pressure turbine and the second low-pressure turbine radially offset from one another relative to a central axis of the aircraft engine.
Claims20
An aircraft engine, comprising:
- a high-pressure spool having a high-pressure turbine drivingly engaged to a high-pressure compressor;
- and
- a low-pressure spool being coaxial with the high-pressure spool, the low-pressure spool having:
- a first low-pressure turbine downstream of the high-pressure turbine;
- and
- a second low-pressure turbine downstream of the first low-pressure turbine, one or more of the first low-pressure turbine and the second low-pressure turbine drivingly engaged to a rotatable load, the first low-pressure turbine and the second low-pressure turbine radially offset from one another relative to a central axis of the aircraft engine, the first low-pressure turbine being coaxial with the second low-pressure turbine.
A turbine section for an aircraft engine, comprising:
- a high-pressure turbine rotatable about a central axis of the aircraft engine;
- a first low-pressure turbine drivingly engageable with a rotatable load and rotatable about the central axis;
- and
- a second low-pressure turbine rotatable about the central axis and in fluid flow communication with the first low-pressure turbine and drivingly engageable with the rotatable load, a flow path extending through the first low-pressure turbine and through the second low-pressure turbine, the flow path extending in a direction being mainly radial relative to a central axis of the turbine section from the first low-pressure turbine to the second low-pressure turbine.
A method of driving a rotatable load of an aircraft engine, comprising:
- flowing combustion gases through a first low-pressure turbine;
- flowing the combustion gases from the first low-pressure turbine to a second low-pressure turbine being radially offset from the first low-pressure turbine relative to a central axis of the aircraft engine, the first low-pressure turbine being coaxial with the second low-pressure turbine;
- and
- driving the rotatable load with one or more of the first low-pressure turbine and the second low-pressure turbine.
Dependencies are inferred from the claim text.