Embedded electric machine
First Claim
1. A gas turbine engine defining a radial direction and an axial direction, the gas turbine engine comprising:
- a fan positioned at a forward end of the gas turbine engine;
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;
a cavity wall defining at least in part a buffer cavity and an electric machine sump, the electric machine sump positioned opposite the buffer cavity and extending at least partially around the electric machine, the buffer cavity surrounding at least a portion of the electric machine and the electric machine sump to thermally insulate the electric machine; and
a cooling duct in airflow communication with the buffer cavity for providing a cooling airflow to the buffer cavity, wherein the cooling duct is additionally in airflow communication with at least one of the fan or the compressor section.
1 Assignment
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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.
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Citations
17 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 fan positioned at a forward end of the gas turbine engine; 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; a cavity wall defining at least in part a buffer cavity and an electric machine sump, the electric machine sump positioned opposite the buffer cavity and extending at least partially around the electric machine, the buffer cavity surrounding at least a portion of the electric machine and the electric machine sump to thermally insulate the electric machine; and a cooling duct in airflow communication with the buffer cavity for providing a cooling airflow to the buffer cavity, wherein the cooling duct is additionally in airflow communication with at least one of the fan or the compressor section. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13)
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14. 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 fan positioned at a forward end of the gas turbine engine; 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; a cavity wall defining at least in part a buffer cavity and an electric machine sump, the electric machine sump positioned opposite the buffer cavity and extending at least partially around the electric machine, the buffer cavity surrounding at least a portion of the electric machine and the electric machine sump to thermally insulate the electric machine; and a cooling duct in airflow communication with the buffer cavity for providing a cooling airflow to the buffer cavity, wherein the cooling duct is additionally in airflow communication with at least one of the fan or the compressor section. - View Dependent Claims (15, 16, 17)
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Specification