A radial flow turbine heat engine includes a compressor, a recuperator, a combustor and a turbine. A compressor outlet manifold collects compressed gas from the compressor through a plurality of compressor outlets. A turbine inlet manifold supplies combustion gas to the turbine through a plurality of turbine inlets. The compressor outlet manifold comprises a plurality of compressor outlet manifold ducts and the turbine inlet manifold comprises a plurality of turbine inlet manifold ducts. These manifold ducts are circumferentially interdigitated with respect of each other around the shaft of the turbine to provide a flow path for compressed gas through the recuperator located radially inwardly with respect to the rotation axis of the shaft compared to the flow path for the combustion gas in the hot side portion of the heat engine. Furthermore, a flow path for the combustion gas is provided to the turbine inlets which are radially inward with respect to the rotation axis of the shaft compared to flow paths for the compressed gas within the compressor outlet manifold proximal to those turbine inlets.

A radial flow turbine heat engine includes a compressor, a recuperator, a combustor and a turbine. A compressor outlet manifold collects compressed gas from the compressor through a plurality of compressor outlets. A turbine inlet manifold supplies combustion gas to the turbine through a plurality of turbine inlets. The compressor outlet manifold comprises a plurality of compressor outlet manifold ducts and the turbine inlet manifold comprises a plurality of turbine inlet manifold ducts. These manifold ducts are circumferentially interdigitated with respect of each other around the shaft of the turbine to provide a flow path for compressed gas through the recuperator located radially inwardly with respect to the rotation axis of the shaft compared to the flow path for the combustion gas in the hot side portion of the heat engine. Furthermore, a flow path for the combustion gas is provided to the turbine inlets which are radially inward with respect to the rotation axis of the shaft compared to flow paths for the compressed gas within the compressor outlet manifold proximal to those turbine inlets.

The present disclosure is directed to a system for bleeding air from a compressed gas path of a gas turbine engine. The system includes an impeller positioned at a downstream end of a compressor in the gas turbine engine. The impeller includes an impeller hub, an impeller arm coupled to the impeller hub, and a plurality of circumferentially spaced apart impeller vanes extending radially outwardly from the impeller arm. The impeller arm defines an impeller arm aperture extending therethrough. A vortex spoiler is positioned radially inwardly from the impeller arm and defines a vortex spoiler passage extending radially therethrough. Bleed air flows from the compressed gas path radially inwardly through both the impeller arm aperture and the vortex spoiler passage.

The present disclosure is directed to a system for bleeding air from a compressed gas path of a gas turbine engine. The system includes an impeller positioned at a downstream end of a compressor in the gas turbine engine. The impeller includes an impeller hub, an impeller arm coupled to the impeller hub, and a plurality of circumferentially spaced apart impeller vanes extending radially outwardly from the impeller arm. The impeller arm defines an impeller arm aperture extending therethrough. A vortex spoiler is positioned radially inwardly from the impeller arm and defines a vortex spoiler passage extending radially therethrough. Bleed air flows from the compressed gas path radially inwardly through both the impeller arm aperture and the vortex spoiler passage.

A turbine engine includes a compressor section, a combustion section, a turbine section, and an exhaust section in serial flow order and together defining a core air flowpath; a fuel delivery system for providing a flow of fuel to the combustion section; and a waste heat recovery system. The waste heat recovery system includes a heat source exchanger in thermal communication with the turbine section, the exhaust section, or both; a heat sink exchanger in thermal communication with the fuel delivery system, the core air flowpath, or both; a thermal transfer bus including a thermal transfer fluid and extending from the heat source exchanger to the heat sink exchanger; and a pump in fluid communication with the thermal transfer bus downstream of the heat source exchanger and upstream of the heat sink exchanger for increasing a temperature and a pressure of the thermal transfer fluid in the thermal transfer bus.

A turbine engine includes a compressor section, a combustion section, a turbine section, and an exhaust section in serial flow order and together defining a core air flowpath; a fuel delivery system for providing a flow of fuel to the combustion section; and a waste heat recovery system. The waste heat recovery system includes a heat source exchanger in thermal communication with the turbine section, the exhaust section, or both; a heat sink exchanger in thermal communication with the fuel delivery system, the core air flowpath, or both; a thermal transfer bus including a thermal transfer fluid and extending from the heat source exchanger to the heat sink exchanger; and a pump in fluid communication with the thermal transfer bus downstream of the heat source exchanger and upstream of the heat sink exchanger for increasing a temperature and a pressure of the thermal transfer fluid in the thermal transfer bus.

A gas turbine engine is provided that includes a compressor section, a turbine section, and a unitary structure. The compressor section has at least one compressor rotor stage. The turbine section has at least one turbine rotor stage. The compressor rotor stage and the turbine rotor stage are in rotational communication with each other. The unitary structure includes an outer case portion, a combustor section, a turbine nozzle, and an exhaust duct. The unitary structure configured for attachment with the turbine section and compressor section.

A gas turbine engine is provided that includes a compressor section, a turbine section, and a unitary structure. The compressor section has at least one compressor rotor stage. The turbine section has at least one turbine rotor stage. The compressor rotor stage and the turbine rotor stage are in rotational communication with each other. The unitary structure includes an outer case portion, a combustor section, a turbine nozzle, and an exhaust duct. The unitary structure configured for attachment with the turbine section and compressor section.

An exoskeletal gas turbine engine having a rotatable outer shaft and an inner stationary case enclosed in a casing. The engine comprises a compressor section at an inlet end, a combustor section, and a turbine section at an outlet end. Rotating compressor blades and turbine blades are attached to, and extend radially inward from, an inner surface of the outer shaft. Stationary vanes are attached, and extend radially outward from, an outer surface of the inner stationary case. The outer shaft rotates around a front bearing and a rear bearing. An inlet compressor blade arrangement is attached to the outer race of the front bearing. An outlet turbine blade arrangement is attached to the outer race of the rear bearing. The inner race of the front and rear bearings attach to the inner stationary case.

An exoskeletal gas turbine engine having a rotatable outer shaft and an inner stationary case enclosed in a casing. The engine comprises a compressor section at an inlet end, a combustor section, and a turbine section at an outlet end. Rotating compressor blades and turbine blades are attached to, and extend radially inward from, an inner surface of the outer shaft. Stationary vanes are attached, and extend radially outward from, an outer surface of the inner stationary case. The outer shaft rotates around a front bearing and a rear bearing. An inlet compressor blade arrangement is attached to the outer race of the front bearing. An outlet turbine blade arrangement is attached to the outer race of the rear bearing. The inner race of the front and rear bearings attach to the inner stationary case.