Thermal management system for a gas turbine engine
First Claim
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1. A thermal management system for a gas turbine engine comprising:
- a forward cover having a filter portion along an axis of rotation of a gas turbine engine, said forward cover at least partially defines a first lubrication passage, a segment of said first lubrication passage is located through a radial cover vane of said forward cover wherein said first lubrication passage defines an annular passage about a second lubrication passage.
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Abstract
A thermal management system and method for a miniature gas turbine engine includes a forward cover having a filter portion along an axis of rotation of a gas turbine engine, a first lubrication passage and a second lubrication passage.
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Citations
21 Claims
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1. A thermal management system for a gas turbine engine comprising:
a forward cover having a filter portion along an axis of rotation of a gas turbine engine, said forward cover at least partially defines a first lubrication passage, a segment of said first lubrication passage is located through a radial cover vane of said forward cover wherein said first lubrication passage defines an annular passage about a second lubrication passage. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11)
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12. A miniature gas turbine engine comprising:
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a rotor shaft defined along an axis of rotation; a compressor wheel mounted to said rotor shaft; a forward bearing which rotationally supports said rotor shaft, said forward bearing comprising an inner race having a multiple of radial apertures; and an aft bearing which rotationally supports said rotor shaft, said forward bearing and said aft rotor shaft bearing in communication with a filtered airflow from said filter portion, said aft bearing comprising an inner race having a multiple of radial apertures; and a forward cover having a filter portion along an axis of rotation of a gas turbine engine, said forward cover defining a first lubrication passage in communication with said multiple of radial apertures in said inner race of said forward bearing and a second lubrication passage in communication with said multiple of radial apertures in said inner race of said aft bearing. - View Dependent Claims (13)
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14. A method of thermal management for a miniature gas turbine engine comprising:
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communicating a cooling airflow through a filter portion of a forward cover along an axis of rotation of a rotor shaft having a compressor wheel, the cooling airflow in communication with a forward bearing and an aft bearing which supports the rotor shaft; directing a lubricant through a first lubricant passage within the forward cover toward the forward bearing; directing the lubricant through a second lubricant passage within the forward cover toward the aft bearing; and merging the cooling airflow into a primary airflow path downstream of the aft bearing, the primary airflow path in communication with the compressor wheel. - View Dependent Claims (15)
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16. A thermal management system for a gas turbine engine comprising:
a forward cover having a filter portion along an axis of rotation of a gas turbine engine, said forward cover at least partially defines a first lubrication passage, a segment of said first lubrication passage is located through a radial cover vane of said forward cover wherein said forward cover is forward of a rotor shaft defined along said axis of rotation, said rotor shaft supported by a forward bearing and an aft bearing and wherein said first lubrication passage is in fluid communication with said forward bearing and a second lubrication passage is in fluid communication with said aft bearing.
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17. A thermal management system for a gas turbine engine comprising:
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a forward cover having a filter portion along an axis of rotation of a gas turbine engine, said forward cover at least partially defines a first lubrication passage, a segment of said first lubrication passage is located through a radial cover vane of said forward cover, a rotor shaft along said axis of rotation; a forward rotor shaft bearing which rotationally supports said rotor shaft; and an aft rotor shaft bearing which rotationally supports said rotor shaft, said forward rotor shaft bearing and said aft rotor shaft bearing in communication with a filtered airflow from said filter portion wherein said forward cover is mounted to a forward housing defined about said axis of rotation, said forward housing having a first housing lubrication passage in communication with said first lubrication passage and a second housing lubrication passage in communication with said second lubrication passage. - View Dependent Claims (18, 19)
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20. A thermal management system for a gas turbine engine comprising:
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a forward cover having a filter portion along an axis of rotation of a gas turbine engine, said forward cover at least partially defines a first lubrication passage, a segment of said first lubrication passage is located through a radial cover vane of said forward cover, a rotor shaft along said axis of rotation; a forward rotor shaft bearing which rotationally supports said rotor shaft; and an aft rotor shaft bearing which rotationally supports said rotor shaft, said forward rotor shaft bearing and said aft rotor shaft bearing in communication with a filtered airflow from said filter portion wherein said forward is cover mounted to a forward housing defined about said axis of rotation, said forward housing having a first housing lubrication passage in communication with said first lubrication passage and a second housing lubrication passage in communication with said second lubrication passage and wherein an inner race of said forward bearing includes a multiple of forward radial apertures and an inner race of said aft bearing includes a multiple of aft radial apertures. - View Dependent Claims (21)
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Specification