Counter-rotating gas turbine engines including turbine sections with separable torque frames

Number of patents in Portfolio can not be more than 2000

United States of America

PATENT NO 12247516
APP PUB NO 20240110504A1
SERIAL NO

17955713

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ATTORNEY / AGENT: (SPONSORED)

Importance

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Abstract

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A gas turbine engine includes a fan located at a forward portion of the gas turbine engine, and a compressor section and a turbine section arranged in serial flow order. The compressor section and the turbine section together define a core airflow path. A rotary member is rotatable with the fan and with a low pressure turbine of the turbine section. The low pressure turbine includes a rotating drum to which a first airfoil structure is connected and extends radially inward toward the rotary member. A torque frame connects the rotating drum to the rotary member and transfers torque from the first airfoil structure mounted to the rotating drum to the rotary member. The torque frame includes an inner disk mounted to the rotary member, an outer ring and a second airfoil structure formed separately from the outer ring and connected thereto by a releasable connecting structure. The second airfoil structure extends radially inward from the outer ring toward the inner disk.

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First Claim

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Patent Owner(s)

  • GENERAL ELECTRIC COMPANY; GE AVIO S.R.L.

International Classification(s)

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  • [Patents Count]

Inventor(s)

Inventor Name Address # of filed Patents Total Citations
Alapati, Ranganayakulu Bangalore, IN 1 0
Antelo, Randy T Silverthorne, US 1 0
D'Ettole, Antonio Giuseppe Rivoli, IT 10 5
Emani, N V Sai Krishna Bengaluru, IN 1 0
Manepalli, Sanjeev Sai Kumar Bangalore, IN 6 9
Mondal, Bhaskar Nanda Bangalore, IN 60 299
Moniz, Thomas Loveland, US 12 518
Pankaj, Peeyush Bangalore, IN 22 73
Shah, Shishir Paresh Bangalore, IN 6 1
Sharma, Praveen Bangalore, IN 79 591
Soni, Anil Bengaluru, IN 2 0

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