17955713. COUNTER-ROTATING GAS TURBINE ENGINES INCLUDING TURBINE SECTIONS WITH SEPARABLE TORQUE FRAMES simplified abstract (GENERAL ELECTRIC COMPANY)

COUNTER-ROTATING GAS TURBINE ENGINES INCLUDING TURBINE SECTIONS WITH SEPARABLE TORQUE FRAMES

Organization Name

GENERAL ELECTRIC COMPANY

Inventor(s)

Ranganayakulu Alapati of Bangalore (IN)

Peeyush Pankaj of Bangalore (IN)

Sanjeev Sai Kumar Manepalli of Bangalore (IN)

Bhaskar Nanda Mondal of Bangalore (IN)

Thomas Moniz of Loveland OH (US)

N V Sai Krishna Emani of Bengaluru (IN)

Shishir Paresh Shah of Bangalore (IN)

Anil Soni of Bengaluru (IN)

Praveen Sharma of Bangalore (IN)

Randy T. Antelo of Silverthorne CO (US)

Antonio Giuseppe D'ettole of Rivoli (IT)

COUNTER-ROTATING GAS TURBINE ENGINES INCLUDING TURBINE SECTIONS WITH SEPARABLE TORQUE FRAMES - A simplified explanation of the abstract

This abstract first appeared for US patent application 17955713 titled 'COUNTER-ROTATING GAS TURBINE ENGINES INCLUDING TURBINE SECTIONS WITH SEPARABLE TORQUE FRAMES

Simplified Explanation

The abstract describes a gas turbine engine with a unique torque frame design connecting the low-pressure turbine to the rotary member.

• The gas turbine engine includes a fan, compressor section, and turbine section in serial flow order.
• The low-pressure turbine has a rotating drum with a first airfoil structure connected to it, transferring torque to the rotary member.
• The torque frame consists of an inner disk connected to the rotary member, an outer ring, and a second airfoil structure connected to the outer ring.
• The second airfoil structure extends radially inward towards the inner disk.

Potential Applications

The innovative torque frame design in this gas turbine engine could potentially be applied in aircraft engines, power generation systems, and marine propulsion systems.

Problems Solved

This technology solves the problem of efficiently transferring torque from the low-pressure turbine to the rotary member in a gas turbine engine.

Benefits

The benefits of this technology include improved engine efficiency, reduced maintenance requirements, and increased overall performance of the gas turbine engine.

Potential Commercial Applications

The unique torque frame design could have commercial applications in the aerospace industry, power generation sector, and marine transportation industry.

Possible Prior Art

One possible prior art could be traditional torque frame designs in gas turbine engines that may not be as efficient or reliable as the one described in this patent application.

How does this torque frame design compare to existing designs in terms of weight and cost?

The abstract does not provide information on the weight and cost implications of this new torque frame design compared to existing designs. Further research or analysis would be needed to answer this question.

What materials are used in the construction of the torque frame and how does it impact the overall performance of the gas turbine engine?

The abstract does not specify the materials used in the torque frame construction or how they affect the engine's performance. Additional details or testing would be required to address this question.

Original Abstract Submitted

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.