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
a cavity wall defining at least in part a buffer cavity, the buffer cavity surrounding at least a portion of the electric machine to thermally insulate the electric machine.
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. A cavity wall defines at least in part a buffer cavity surrounding at least a portion of the electric machine to thermally insulate the electric machine, e.g., from the relatively high temperatures within the core air flowpath.
23 Citations
20 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 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 a cavity wall defining at least in part a buffer cavity, the buffer cavity surrounding at least a portion of the electric machine to thermally insulate the electric machine. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14, 15, 16)
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17. 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 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, the electric machine electrically connected to the electric propulsor; and a cavity wall defining at least in part a buffer cavity, the buffer cavity surrounding at least a portion of the electric machine to thermally insulate the electric machine. - View Dependent Claims (18, 19, 20)
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Specification