Turbine engine with a turbo-compressor
AssigneeUnited Technologies Corporation
InventorsDaniel B. Kupratis, William G. Sheridan
Life of this patent
Estimating the term…
Abstract
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.
Claims13
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.
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.
Dependencies are inferred from the claim text.