Aircraft air system with boost compressor(s)

1 . A system for an aircraft powerplant, comprising:

a turbine engine including a core flowpath, a first rotating structure, a compressor section, a combustor section and a turbine section, the core flowpath extending through the compressor section, the combustor section and the turbine section from an airflow inlet into the core flowpath to a combustion products exhaust from the core flowpath, and the first rotating structure comprising a first bladed rotor arranged along the core flowpath in the compressor section or the turbine section; and

an accessory system including a first electromechanical apparatus, an air circuit and an air device, the first electromechanical apparatus including a first electric machine and a first boost compressor, the first electric machine comprising a first electric machine rotor that is operatively coupled to the first rotating structure, the first boost compressor comprising a first boost compressor rotor that is operatively and mechanically coupled to the first electric machine rotor and the first rotating structure, and the air circuit configured to direct air received from an air source, through the first boost compressor, to the air device;

wherein one of

the first boost compressor rotor is operatively and mechanically coupled to the first rotating structure through the first electric machine rotor; or

the first electric machine rotor is operatively and mechanically coupled to the first rotating structure through the first boost compressor rotor.

2 . The system of claim 1 , wherein the first boost compressor rotor is coaxial with the first electric machine rotor.

3 . The system of claim 1 , wherein the first electromechanical apparatus is configured such that the first electric machine rotor and the first boost compressor rotor rotate at a common rotational speed.

4 . The system of claim 1 , wherein the first boost compressor rotor is mechanically coupled to the first electric machine rotor through a clutch.

5 . The system of claim 1 , further comprising:

an accessory gearbox;

the first electromechanical apparatus mounted to the accessory gearbox; and

the first electromechanical apparatus operatively coupled to the first rotating structure through the accessory gearbox.

6 . The system of claim 1 , wherein

the first rotating structure is configured to drive rotation of the first electric machine rotor and the first boost compressor rotor during a first mode of operation; and

the first electric machine rotor is configured to drive rotation of the first boost compressor rotor during a second mode of operation.

7 . The system of claim 1 , further comprising a bypass flowpath bypassing at least one of the compressor section, the combustor section or the turbine section, wherein the bypass flowpath is configured as the air source.

8 . The system of claim 7 , further comprising:

a housing structure forming a radial peripheral boundary of the bypass flowpath;

wherein an airflow inlet into the air circuit is disposed with the housing structure at the radial peripheral boundary of the bypass flowpath.

9 . The system of claim 7 , further comprising:

a vane structure extending radially across the bypass flowpath;

wherein an airflow inlet into the air circuit is disposed with the vane structure.

10 . The system of claim 1 , further comprising a heat exchanger fluidly coupled along the air circuit downstream of the first boost compressor.

11 . The system of claim 1 , further comprising a housing structure comprising an internal compartment radially outboard of a core of the turbine engine, the core of the turbine engine including the compressor section, the combustor section and the turbine section, and the air device configured to direct the air into the internal compartment.

12 . The system of claim 1 , further comprising a clearance control system for the turbine engine, the clearance control system comprising the air device.

13 . The system of claim 1 , wherein the air device is configured to direct the air into a plenum next to the first electric machine to cool the first electric machine.

14 . The system of claim 1 , further comprising a flow regulator fluidly coupled along the air circuit upstream of the first boost compressor.

15 . A system for an aircraft powerplant, comprising:

a turbine engine including a core flowpath, a first rotating structure, a compressor section, a combustor section and a turbine section, the core flowpath extending through the compressor section, the combustor section and the turbine section from an airflow inlet into the core flowpath to a combustion products exhaust from the core flowpath, and the first rotating structure comprising a first bladed rotor arranged along the core flowpath in the compressor section or the turbine section; and

an accessory system including a first electromechanical apparatus, an air circuit and an air device, the first electromechanical apparatus including a first electric machine and a first boost compressor, the first electric machine comprising a first electric machine rotor that is operatively coupled to the first rotating structure, the first boost compressor comprising a first boost compressor rotor that is operatively coupled to the first electric machine rotor and the first rotating structure, and the air circuit configured to direct air received from an air source, through the first boost compressor, to the air device;

wherein the turbine engine further includes a second rotating structure, and the second rotating structure comprises a second bladed rotor arranged along the core flowpath in the compressor section or the turbine section;

wherein the accessory system further includes a second electromechanical apparatus, the second electromechanical apparatus includes a second electric machine and a second boost compressor, the second electric machine comprises a second electric machine rotor that is operatively coupled to the second rotating structure, and the second boost compressor comprises a second boost compressor rotor that is operatively coupled to the second electric machine rotor and the second rotating structure; and

wherein the air circuit is configured to further direct the air received from the air source, through the second boost compressor, to the air device.

16 . A system for an aircraft powerplant, comprising:

a turbine engine including a core flowpath, a first rotating structure, a compressor section, a combustor section and a turbine section, the core flowpath extending through the compressor section, the combustor section and the turbine section from an airflow inlet into the core flowpath to a combustion products exhaust from the core flowpath, and the first rotating structure comprising a first bladed rotor arranged along the core flowpath in the compressor section or the turbine section; and

an accessory system including a first electromechanical apparatus, an air circuit and an air device, the first electromechanical apparatus including a first electric machine and a first boost compressor, the first electric machine comprising a first electric machine rotor that is operatively coupled to the first rotating structure, the first boost compressor comprising a first boost compressor rotor that is operatively coupled to the first electric machine rotor and the first rotating structure, and the air circuit configured to direct air received from an air source, through the first boost compressor, to the air device;

wherein the turbine engine further includes a second rotating structure, and the second rotating structure comprises a second bladed rotor arranged along the core flowpath in the compressor section or the turbine section;

wherein the accessory system further includes a second electromechanical apparatus, the second electromechanical apparatus includes a second electric machine and a second boost compressor, the second electric machine comprises a second electric machine rotor that is operatively coupled to the second rotating structure, and the second boost compressor comprises a second boost compressor rotor that is operatively coupled to the second electric machine rotor and the second rotating structure; and

wherein the air circuit is configured to further direct the air received from the air source, through the second boost compressor, to a second air device.