EMBEDDED ELECTRIC MACHINE
First Claim
1. A gas turbine engine defining a radial direction and an axial direction, the gas turbine engine comprising:
- a compressor section and a turbine section arranged in serial flow order, the compressor section and turbine section together defining a core air flowpath;
a rotary component rotatable with at least a portion of the compressor section and with at least a portion of the turbine section;
an electric machine coupled to the rotary component at least partially inward of the core air flowpath along the radial direction; and
an electric communication bus electrically connected to the electric machine, at least a portion of the electric communication bus extending through the core air flowpath.
1 Assignment
0 Petitions
Accused Products
Abstract
A gas turbine engine includes a compressor section and a turbine section together defining a core air flowpath. Additionally, a rotary component is rotatable with at least a portion of the compressor section and at least a portion of the turbine section. An electric machine is mounted coaxially with the rotary component and positioned at least partially inward of the core air flowpath along a radial direction of the gas turbine engine. An electric communication bus is electrically connected to the electric machine and extends through the core air flowpath to, e.g., electrically connect the electric machine to one or more systems of the gas turbine engine or a propulsion system including the gas turbine engine.
21 Citations
20 Claims
-
1. A gas turbine engine defining a radial direction and an axial direction, the gas turbine engine comprising:
-
a compressor section and a turbine section arranged in serial flow order, the compressor section and turbine section together defining a core air flowpath; a rotary component rotatable with at least a portion of the compressor section and with at least a portion of the turbine section; an electric machine coupled to the rotary component at least partially inward of the core air flowpath along the radial direction; and an electric communication bus electrically connected to the electric machine, at least a portion of the electric communication bus extending through the core air flowpath. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14, 15)
-
-
16. A propulsion system for an aeronautical device comprising:
-
an electric propulsor; and a gas turbine engine defining a radial direction and an axial direction, the gas turbine engine comprising a compressor section and a turbine section arranged in serial flow order, the compressor section and turbine section together defining a core air flowpath; a rotary component rotatable with at least a portion of the compressor section and with at least a portion of the turbine section; an electric machine coupled to the rotary component at least partially inward of the core air flowpath along the radial direction; and an electric communication bus electrically connecting the electric machine to the electric propulsor, at least a portion of the electric communication bus extending through the core air flowpath. - View Dependent Claims (17, 18, 19, 20)
-
Specification