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US Patent 11549373 Reduced deflection turbine rotor

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Is a
Patent
Patent
1

Patent attributes

Patent Jurisdiction
United States Patent and Trademark Office
United States Patent and Trademark Office
1
Patent Number
115493731
Patent Inventor Names
Michael G. McCaffrey1
Date of Patent
January 10, 2023
1
Patent Application Number
171233441
Date Filed
December 16, 2020
1
Patent Citations
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US Patent 10724380 CMC blade with internal support
1
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US Patent 10794188 Rotor blade assembly comprising a ring-shaped or disc-shaped blade carrier and a radially inner reinforcement structure
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US Patent 10161773 Methods and apparatus to determine airflow conditions at an inlet of an engine
1
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US Patent 10358924 Turbofan arrangement with blade channel variations
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US Patent 10371047 Geared turbofan engine with targeted modular efficiency
1
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US Patent 10371061 Turbine section of high bypass turbofan
Patent Primary Examiner
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Loren C Edwards
1
CPC Code
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F01D 11/22
1
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F01D 25/16
1
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F01D 25/28
1
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F05D 2240/24
1
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F05D 2240/307
1
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F01D 5/025
1
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F05D 2260/30
1
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F02C 7/06
1
...

A turbine section for a gas turbine engine according to an example of the present disclosure includes, among other things, a first turbine rotor coupled to a first turbine shaft. The first turbine shaft is rotatable about a longitudinal axis. A second turbine rotor is coupled to a second turbine shaft. The second turbine shaft is rotatable about the longitudinal axis, and the second turbine rotor is axially aft of the first turbine rotor relative to the longitudinal axis. An aft bearing assembly rotatably supports the second turbine shaft. The second turbine rotor includes a disk assembly that carries at least one row of turbine blades. The disk assembly is mechanically attached to the second turbine shaft at an attachment point. The attachment point is axially aft of the aft bearing assembly such that an aft portion of the second turbine shaft is cantilevered from the aft bearing system with respect to the longitudinal axis. The disk assembly includes a metallic material. Each of the turbine blades comprises a ceramic matrix composite (CMC) material.

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