A turbomachine comprises a flow duct with coaxially arranged radially inner and outer endwalls, first and second sets of axially spaced rotor stages arranged between the inner and outer endwalls, and a plurality of variable endwall segments arranged along the inner endwall. The first set of rotor st
A turbomachine comprises a flow duct with coaxially arranged radially inner and outer endwalls, first and second sets of axially spaced rotor stages arranged between the inner and outer endwalls, and a plurality of variable endwall segments arranged along the inner endwall. The first set of rotor stages rotates in a first direction, and the second set rotates in a second direction. The first and second sets alternate in axial series along the flow duct, such that axially adjacent rotor stages rotate in different directions. The variable endwall segments are radially positionable, in order to regulate loading on the first and second sets of rotor stages by changing a cross-sectional flow area between the inner and outer endwalls.
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1. A turbomachine comprising: a flow duct comprising coaxially arranged radially inner and outer endwalls;a first set of axially spaced rotor stages arranged between the inner and outer endwalls, each of the first set of rotor stages rotating in a first direction;a second set of axially spaced rotor
1. A turbomachine comprising: a flow duct comprising coaxially arranged radially inner and outer endwalls;a first set of axially spaced rotor stages arranged between the inner and outer endwalls, each of the first set of rotor stages rotating in a first direction;a second set of axially spaced rotor stages arranged between the inner and outer endwalls, each of the second set of rotor stages rotating in a second direction;wherein the first and second sets of rotor stages alternate in axial series, such that axially adjacent rotor stages rotate in different directions; anda set of variable endwall segments arranged along the inner endwall of the flow duct, wherein the variable endwall segments are radially positionable to regulate loading on the first and second sets of rotor stages by changing a flow area between the inner and outer endwalls. 2. The turbomachine of claim 1, further comprising an inner spool coupled to each of the first set of rotor stages in a radially inner region, the inner spool co-rotating with the first set of rotor stages. 3. The turbomachine of claim 2, further comprising an outer spool arranged coaxially about the inner spool and coupled to each of the second set of rotor stages in a radially outer region, the outer spool counter-rotating with the second set of rotor stages. 4. The turbomachine of claim 2, further comprising platform gear mechanisms coupling the inner spool to each of the second set of rotor stages in a radially inner platform region, such that the second set of rotor stages counter-rotate about the inner spool. 5. The turbomachine of claim 4, wherein the platform gear mechanisms are configured to counter-rotate the second set of rotor stages at different speeds about the inner spool. 6. The turbomachine of claim 1, wherein the first and second set of rotor stages form a compressor section and a turbine section in axial series along the flow duct. 7. The turbomachine of claim 6, wherein the first and second pluralities of rotor stages alternate in an axially adjacent series in each of the compressor section and the turbine section, such that axially adjacent compressor rotor stages rotate in different directions and axially adjacent turbine rotor stages alternate in different directions. 8. The turbomachine of claim 7, further comprising an inner spool coupling a compressor rotor stage in the first set of rotor stages to a turbine rotor stage in the first set of rotor stages, such that the compressor rotor stage co-rotates with the turbine rotor stage. 9. The turbomachine of claim 7, further comprising inter-row gear mechanisms coupling the first set of rotor stages to the second set of rotor stages, such that axially adjacent compressor and turbine rotor stages rotate in opposite directions. 10. The turbomachine of claim 7, further comprising inter-row gear mechanisms coupling the first set of rotor stages to the second set of rotor stages in the turbine section, such that the axially adjacent turbine rotor stages rotate in opposite directions. 11. The turbomachine of claim 1, further comprising blade tip gear mechanisms coupling the second set of rotor stages to a stationary casing, the stationary casing arranged coaxially about the first and second pluralities of turbine rotor stages. 12. The turbomachine of claim 1, wherein the variable endwall segments comprise n-shaped members having two radial legs and an axial surface, the axial surfaces of the n-shaped members being positionable in the radial direction to increase or decrease the flow area. 13. The turbomachine of claim 1, wherein the variable endwall segments comprise t-shaped members having a radial leg and an axial surface, the axial surfaces of the t-shaped members being positionable in the radial direction to increase or decrease the flow area. 14. The turbomachine of claim 1, wherein the variable endwall segments comprise arcuate elements forming a disc-shaped variable inner endwall, the variable inner endwall being positionable in the radial direction to increase or decrease the flow area. 15. The turbomachine of claim 1, further comprising radial slots formed in airfoil components of the first set of rotor stages, the variable endwall segments being positionable in the radial direction along the radial slots. 16. An engine comprising: a flow duct comprising an inner flow boundary arranged about an axis and an outer flow boundary coaxially arranged about the inner flow boundary;a compressor section comprising co-rotating compressor rotor stages interspersed with counter-rotating compressor rotor stages in series along the axis of the flow duct, wherein axially adjacent compressor rotor stages rotate in opposite directions about the axis;a turbine section comprising co-rotating turbine rotor stages interspersed with counter-rotating turbine rotor stages in series along the axis of the flow duct, wherein axially adjacent turbine rotor stages rotate in opposite directions about the axis; anda variable inner endwall comprising inner endwall segments, each of the inner endwall segments being radially positionable to regulate loading in the compressor and turbine sections by changing a flow area between the variable inner endwall and the outer flow boundary. 17. The engine of claim 16, further comprising a co-rotating spool coupling the co-rotating compressor rotor stages to the co-rotating turbine rotor stages. 18. The engine of claim 17, further comprising a counter-rotating spool coupling the counter-rotating compressor rotor stages to the counter-rotating turbine rotor stages. 19. The engine of claim 17, further comprising gear mechanisms coupling the co-rotating spool to the counter-rotating compressor and turbine rotor stages, such that the counter-rotating compressor and turbine rotor stages counter-rotate about the co-rotating spool. 20. The engine of claim 16, further comprising gear mechanisms coupling the co-rotating compressor and turbine rotor stages to the counter-rotating compressor and turbine rotor stages, such that the axially adjacent compressor and turbine rotor stages rotate in opposite directions. 21. A gas turbine engine comprising: a flow duct;a compressor section comprising a plurality of co-rotating compressor rotor stages interspersed with a plurality of counter-rotating compressor rotor stages, such that axially adjacent compressor rotor stages rotate in opposite directions; anda turbine section comprising a plurality of co-rotating turbine rotor stages interspersed with a plurality of counter-rotating turbine rotor stages, such that axially adjacent turbine rotor stages rotate in opposite directions;a variable inner endwall comprising a plurality of inner endwall segments circumferentially arranged about an inner diameter of the flow duct, wherein the inner endwall segments are positionable in a radial direction to regulate loading on the compressor and turbine sections by changing a cross-sectional area of the flow duct. 22. The gas turbine engine of claim 21, further comprising a spool coupling the co-rotating compressor rotor stages to the co-rotating turbine rotor stages. 23. The gas turbine engine of claim 22, further comprising gearing mechanisms coupling the spool to the counter-rotating compressor and turbine rotor stages, such that the counter-rotating compressor and turbine rotor stages counter-rotate about the spool. 24. The gas turbine engine of claim 21, further comprising a propulsion rotor coupled to the compressor section. 25. The gas turbine engine of claim 24, further comprising radial slots in airfoil members of the counter-rotating turbine rotor stages, wherein the inner endwall segments are positionable in the radial direction along the radial slots to control loading on the propulsion rotor.
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이 특허에 인용된 특허 (12)
Cycon James P. (Orange CT) Kohlhepp Fred W. (Hamden CT) Millea Vincent F. (Stratford CT), Coaxial transmission/center hub subassembly for a rotor assembly having ducted, coaxial counter-rotating rotors.
Krauss Timothy A. (Harwinton CT) Hunter David H. (Cheshire CT) Beatty Robert D. (Trumbull CT), Rotor blade subassembly for a rotor assembly having ducted, coaxial counter-rotating rotors.
Cycon James P. (Orange CT) Hunter David H. (Cheshire CT) Krauss Timothy A. (Harwinton CT), Snubber assembly for a rotor assembly having ducted, coaxial counter-rotating rotors.
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