Turbine engine with a turbo-compressor
A turbine engine is provided that includes a turbo-compressor, a combustor section, a flow path and a recuperator. The turbo-compressor includes a compressor section and a turbine section. The combustor section includes a combustor and a plenum adjacent the combustor. The flow path extends through the compressor section, the combustor section and the turbine section. The recuperator is configured with the flowpath between the combustor section and the turbine section. An inlet duct to the recuperator is fluidly coupled with the flow path upstream of the plenum. An outlet duct from the recuperator is fluidly coupled with the plenum.
1. A turbine engine, comprising:
a turbo-compressor including a compressor section and a turbine section, the turbo-compressor including a rotor that comprises a rotor disk, a plurality of compressor blades and a plurality of turbine blades positioned radially outboard of the compressor blades, each of the compressor blades connecting a respective one of the turbine blades to the rotor disk;
a combustor section including a combustor and a plenum adjacent the combustor;
a second compressor section fluidly coupled between the compressor section and the combustor section, the second compressor section fluidly downstream of the compressor blades;
a flow path extending through the compressor section, the second compressor section, the combustor section and the turbine section; and
a recuperator configured within the flow path between the combustor section and the turbine section, wherein an inlet duct to the recuperator is fluidly coupled with the flow path upstream of the plenum and configured to direct a portion of compressed air flowing through the flow path to the recuperator, and an outlet duct from the recuperator is fluidly coupled with the plenum.
2. The turbine engine of claim 1 , wherein the recuperator is arranged within the flow path.
3. The turbine engine of claim 1 , wherein the recuperator comprises a crossflow heat exchanger.
4. The turbine engine of claim 1 , further comprising a second recuperator configured with the flow path between the combustor section and the turbine section, wherein a second inlet duct to the second recuperator is fluidly coupled with the flow path upstream of the plenum, and a second outlet duct from the second recuperator is fluidly coupled with the plenum.
5. The turbine engine of claim 4 , wherein the recuperator and the second recuperator are disposed longitudinally along the flow path.
6. The turbine engine of claim 4 , wherein the recuperator and the second recuperator are disposed circumferentially about a centerline of the turbine engine.
7. The turbine engine of claim 1 , wherein the inlet duct is fluidly coupled with the flow path at a downstream end of the second compressor section.
8. The turbine engine of claim 1 , further comprising a bypass duct that branches off from the inlet duct and is fluidly coupled with a stator vane arrangement located downstream of the combustor section.
9. The turbine engine of claim 1 , further comprising a fan section, wherein the rotor of the turbo-compressor is connected to a rotor of the fan section.
10. The turbine engine of claim 9 , further comprising a gear train that connects the rotor of the turbo-compressor to the rotor of the fan section.
11. The turbine engine of claim 1 , wherein the flow path includes an annular forward flow section and an annular reverse flow section which is radially outboard of the forward flow section.
12. The turbine engine of claim 1 , further comprising a second turbine section fluidly coupled between the combustor section and the turbine section and upstream of the recuperator.
13. A turbine engine, comprising:
a turbo-compressor including a compressor section and a turbine section, the turbo-compressor including a rotor that comprises a rotor disk, a plurality of compressor blades of the compressor section and a plurality of turbine blades of the turbine section positioned radially outboard of the compressor blades, each of the compressor blades connecting a respective one of the turbine blades to the rotor disk;
a combustor section including a combustor and a plenum adjacent the combustor;
a second turbine section fluidly coupled between the combustor section and the turbine section;
a flow path extending through the compressor section, the combustor section, the second turbine section and the turbine section; and
a recuperator configured within the flow path between the combustor section and the turbine section, wherein an inlet duct to the recuperator is fluidly coupled with the flow path upstream of the plenum and configured to direct a portion of compressed air flowing through the flow path to the recuperator, and an outlet duct from the recuperator is fluidly coupled with the plenum;
wherein the second turbine section is upstream of the recuperator.