A by-pass turbofan gas turbine engine, has a by-pass fan, a generally annular core engine duct, a generally annular by-pass duct situated in a generally coaxial relationship with the core engine duct coupled to the by-pass fan, an upstream axial compressor coupled to the core engine duct, a downstre
A by-pass turbofan gas turbine engine, has a by-pass fan, a generally annular core engine duct, a generally annular by-pass duct situated in a generally coaxial relationship with the core engine duct coupled to the by-pass fan, an upstream axial compressor coupled to the core engine duct, a downstream radial compressor coupled to the upstream compressor, a generally annular recuperator with a cool side inlet coupled to the downstream compressor, a generally annular combustor coupled to a cool side outlet of the recuperator, a radial turbine coupled to the combustor and a warm side inlet of the recuperator coupled to the radial turbine, at least one exhaust nozzle coupled to a warm side outlet of the recuperator that discharges into the by-pass duct and a propelling nozzle coupled to the by-pass duct.
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1. A by-pass turbofan gas turbine engine, comprising: a by-pass fan with a by-pass fan outlet;a generally annular core engine duct with a core engine duct inlet coupled to the by-pass fan outlet and a core engine duct outlet;a generally annular by-pass duct situated in a generally coaxial relationsh
1. A by-pass turbofan gas turbine engine, comprising: a by-pass fan with a by-pass fan outlet;a generally annular core engine duct with a core engine duct inlet coupled to the by-pass fan outlet and a core engine duct outlet;a generally annular by-pass duct situated in a generally coaxial relationship with the core engine duct and with a by-pass duct inlet coupled to the by-pass fan outlet and a by-pass duct outlet;an upstream axial compressor with an axial upstream compressor inlet coupled to the core engine duct outlet and an axial upstream compressor outlet;a downstream radial compressor with an axial downstream compressor inlet coupled to the upstream compressor outlet and a radial downstream compressor outlet;a generally annular recuperator with a cool side inlet coupled to the downstream compressor outlet, a cool side outlet, a warm side inlet and a warm side outlet;a generally annular combustor with a combustor inlet coupled to the recuperator cool side outlet and a combustor outlet;a radial turbine with a radial turbine inlet coupled to the combustor outlet and a turbine outlet coupled to the recuperator warm side inlet;at least one exhaust nozzle with an exhaust nozzle inlet coupled to the recuperator warm side outlet and an exhaust nozzle outlet that discharges into the by-pass duct upstream of the axial upstream compressor outlet; anda propelling nozzle coupled to the by-pass duct outlet. 2. The engine of claim 1, wherein a manifold couples the by-pass fan outlet to the core engine duct inlet and the by-pass duct inlet. 3. The engine of claim 1, wherein the recuperator borders the upstream and downstream compressors. 4. The engine of claim 1, wherein the by-pass duct borders the recuperator. 5. The engine of claim 1, further comprising a drive shaft with a drive shaft axis of rotation that couples the turbine to the upstream compressor and the downstream compressor. 6. The engine of claim 5, wherein the by-pass fan couples to the drive shaft. 7. The engine of claim 6, further comprising an epicyclic gear train that couples the by-pass fan to the drive shaft, wherein the by-pass fan has a fan axis of rotation generally coincident with the drive shaft axis of rotation. 8. The engine of claim 1, further comprising an upstream baffle for coupling the downstream compressor outlet to the recuperator cool side inlet and the recuperator warm side outlet to each exhaust nozzle inlet. 9. The engine of claim 1, further comprising a downstream baffle for coupling the recuperator cool side outlet to the combustor inlet and the combustor outlet to the recuperator warm side inlet. 10. The engine of claim 1, wherein each exhaust nozzle comprises a mixing nozzle. 11. The engine of claim 1, wherein the each exhaust nozzle outlet is situated upstream of the recuperator. 12. A by-pass turbofan gas turbine engine, comprising: a by-pass fan with a by-pass fan outlet;a generally annular core engine duct with a core engine duct inlet and a core engine duct outlet;a generally annular by-pass duct situated in a generally coaxial relationship with the core engine duct and with a by-pass duct inlet and a by-pass duct outlet;a manifold that couples the by-pass fan outlet to the core engine duct inlet and the by-pass duct inlet;an upstream axial compressor with an axial upstream compressor inlet coupled to the core engine duct outlet and an axial upstream compressor outlet;a downstream radial compressor with an axial downstream compressor inlet coupled to the upstream compressor outlet and a radial downstream compressor outlet;a generally annular recuperator with a cool side inlet, a cool side outlet, a warm side inlet and a warm side outlet;a generally annular combustor with a combustor inlet and a combustor outlet;a radial turbine with a radial turbine inlet coupled to the combustor outlet and a turbine outlet;a drive shaft with a drive shaft axis of rotation that couples the turbine to the upstream compressor and the downstream compressor;at least one exhaust nozzle with an exhaust nozzle inlet coupled to an exhaust nozzle outlet that discharges into the by-pass duct upstream of the axial upstream compressor outlet;an upstream baffle that couples the downstream compressor outlet to the recuperator cool side inlet and the recuperator warm side outlet to each exhaust nozzle inlet;a downstream baffle for coupling the recuperator cool side outlet to the combustor inlet and the combustor outlet to the recuperator warm side inlet; anda propelling nozzle coupled to the by-pass duct outlet. 13. The engine of claim 12, wherein the by-pass fan couples to the drive shaft. 14. The engine of claim 13, further comprising an epicyclic gear train that couples the by-pass fan to the drive shaft, wherein the by-pass fan has a fan axis of rotation generally coincident with the drive shaft axis of rotation. 15. The engine of claim 12, wherein the recuperator borders the upstream and downstream compressors. 16. The engine of claim 12, wherein the by-pass duct borders the recuperator. 17. The engine of claim 12, wherein each exhaust nozzle comprises a mixing nozzle. 18. The engine of claim 12, wherein the each exhaust nozzle outlet is situated upstream of the recuperator. 19. A by-pass turbofan gas turbine engine, comprising: a by-pass fan with a by-pass fan axis of rotation and a by-pass fan outlet;a generally annular core engine duct with a core engine duct inlet and a core engine duct outlet;a generally annular by-pass duct situated in a generally coaxial relationship with the core engine duct and with a by-pass duct inlet and a by-pass duct outlet;a manifold that couples the by-pass fan outlet to the core engine duct inlet and the by-pass duct inlet;an upstream axial compressor with an axial upstream compressor inlet coupled to the core engine duct outlet and an axial upstream compressor outlet;a downstream radial compressor with an axial downstream compressor inlet coupled to the upstream compressor outlet and a radial downstream compressor outlet;a generally annular recuperator with a cool side inlet, a cool side outlet, a warm side inlet and a warm side outlet;a generally annular combustor with a combustor inlet and a combustor outlet;a radial turbine with a radial turbine inlet coupled to the combustor outlet and a turbine outlet;a drive shaft with a drive shaft axis of rotation generally coincident with the fan axis of rotation that couples the turbine to the upstream compressor and the downstream compressor;an epicyclic gear train that couples the by-pass fan to the drive shaft;at least one exhaust nozzle with an exhaust nozzle inlet and an exhaust nozzle outlet that discharges into the by-pass duct upstream of the axial upstream compressor outlet;an upstream baffle that couples the downstream compressor outlet to the recuperator cool side inlet and the recuperator warm side outlet to each exhaust nozzle inlet;a downstream baffle for coupling the recuperator cool side outlet to the combustor inlet and the combustor outlet to the recuperator warm side inlet; anda propelling nozzle coupled to the by-pass duct outlet. 20. The engine of claim 19, wherein the recuperator borders the upstream and downstream compressors. 21. The engine of claim 19, wherein the by-pass duct borders the recuperator. 22. The engine of claim 19, wherein each exhaust nozzle comprises a mixing nozzle. 23. The engine of claim 19, wherein the each exhaust nozzle outlet is situated upstream of the recuperator.
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