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, a turbine section, and an exhaust section arranged in serial flow order, the compressor section, a turbine section, and an exhaust 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, the electric machine mounted at least partially within or aft of the turbine section along the axial direction;
an electric communication bus electrically connected to the electric machine and including an intermediate section, the intermediate section extending through the core air flowpath at a location within at least one of the turbine section or the exhaust section; and
a cooling system for cooling at least a portion of the intermediate section of the electric communication bus.
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.
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Citations
16 Claims
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1. A gas turbine engine defining a radial direction and an axial direction, the gas turbine engine comprising:
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a compressor section, a turbine section, and an exhaust section arranged in serial flow order, the compressor section, a turbine section, and an exhaust 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, the electric machine mounted at least partially within or aft of the turbine section along the axial direction; an electric communication bus electrically connected to the electric machine and including an intermediate section, the intermediate section extending through the core air flowpath at a location within at least one of the turbine section or the exhaust section; and a cooling system for cooling at least a portion of the intermediate section of the electric communication bus. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12)
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13. A propulsion system for an aeronautical device comprising:
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an electric propulsor; and a gas turbine engine defining a radial direction and an axial direction, the gas turbine engine comprising a compressor section, a turbine section, and an exhaust section arranged in serial flow order, the compressor section, a turbine section, and an exhaust 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, the electric machine mounted at least partially within or aft of the turbine section along the axial direction; an electric communication bus electrically connecting the electric machine to the electric propulsor and including an intermediate section, the intermediate section extending through the core air flowpath at a location within at least one of the turbine section or the exhaust section; and a cooling system for cooling at least a portion of the intermediate section of the electric communication bus. - View Dependent Claims (14, 15, 16)
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Specification