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US 10,329,943 B2Granted
Split axial-centrifugal compressor
AssigneesRolls-Royce North American Technologies Inc., ROLLS-ROYCE plc
InventorsAndrew J. Eifert, Craig E. Heathco, Robert W. Cedoz, Robert T. Duge
Life of this patent
Estimating the term…
Abstract
A gas turbine engine including a compressor, a turbine, and a variable-ratio unit is disclosed. The turbine is coupled to the compressor to drive rotation of multiple stages of the compressor. The variable-ratio unit is configured to transmit rotational power from the turbine to at least one stage of the compressor to drive rotation of the at least one stage of the compressor.
Claims16
A gas turbine engine comprising
- a compressor including an axial compression stage and a centrifugal compression stage arranged aft of the axial compression stage along an engine axis,
- a turbine arranged aft of the centrifugal compression stage and coupled to the compressor to drive rotation of the axial compression stage and the centrifugal compression stage about the engine axis, and
- a variable-ratio unit coupled to the turbine and the compressor, the variable-ratio unit configured to transmit rotational power generated by the turbine about the engine axis to the axial compression stage to drive rotation of the axial compression stage at various speeds offset from a turbine speed,
- wherein the axial compression stage has an outlet radius and the centrifugal compression stage has an inlet radius that is about equal to the outlet radius of the axial compression stage to facilitate a smooth transition of air from the axial compression stage to the centrifugal compression stage, the centrifugal compression stage is coupled to the turbine for common rotation therewith about the engine axis, and the variable-ratio unit is arranged forward of the axial compression stage about the engine axis.
1 more element
A compressor comprising
- an axial compression stage having an axial inlet and an axial outlet,
- a centrifugal compression stage having a centrifugal inlet and a centrifugal outlet, and
- a variable-ratio unit adapted to receive rotational power and distribute the rotational power between the axial compression stage and the centrifugal compression stage, the variable-ratio unit including an input and an output, the output coupled between the input and one of the axial compression stage and the centrifugal compression stage,
- wherein the centrifugal inlet is arranged to receive compressed air discharged from the axial outlet and has a first area about equal to a second area of the axial outlet, the axial compression stage is arranged forward of the centrifugal compression stage, and the variable-ratio unit is arranged forward of the axial compression stage.
1 more element
A gas turbine engine comprising
- a compressor including an axial compression stage and a centrifugal compression stage arranged aft of the axial compression stage along an engine axis,
- a turbine arranged aft of the centrifugal compression stage, the turbine including a single turbine stage coupled to each of the axial compression stage and the centrifugal compression stage to drive rotation of each of the axial compression stage and the centrifugal compression stage about the engine axis, and
- a variable-ratio unit coupled to the turbine and the compressor, the variable-ratio unit configured to transmit rotational power generated by the turbine about the engine axis to at least one of the axial compression stage and the centrifugal compression stage to drive rotation of the at least one of the axial compression stage and the centrifugal compression stage at various speeds offset from a turbine speed.
Dependencies are inferred from the claim text.