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.
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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.
67 Citations
19 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. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14, 15)
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16. 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 (17)
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18. 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 (19)
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Specification