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

Patent metadata

Field	Value
Publication number	US-12247516-B2
Application number	US-202217955713-A
Country	US
Kind code	B2
Filing date	Sep 29, 2022
Priority date	Sep 29, 2022
Publication date	Mar 11, 2025
Grant date	Mar 11, 2025

Abstract

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.

First claim

What is claimed is:

1. A gas turbine engine comprising:
a fan located at a forward portion of the gas turbine engine;
a compressor section and a turbine section arranged in serial flow order, the compressor section and the turbine section together defining a core airflow path;
a rotary member rotatable with the fan and with a low pressure turbine of the turbine section;
the low pressure turbine comprising a rotating drum to which a first airfoil structure is connected and extends radially inward toward the rotary member; and
a torque frame that 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 comprising:
an inner disk mounted to the rotary member;
an outer ring formed as a single monolithic piece; and
a second airfoil structure formed separately from the outer ring and connected thereto by a releasable connecting structure configured to extend radially through an outer face of the outer ring, the second airfoil structure extending radially inward from the outer ring toward the inner disk;
wherein the second airfoil structure is part of a structural member that is formed separately from the outer ring and inner disk, the structural member is releasably connected to the outer ring and the inner disk and comprises an outer tip plate that engages the outer ring and an inner tip plate that engages the inner disk;
wherein the releasable connecting structure comprises an attachment tab that projects radially outward from the outer tip plate, the attachment tab configured to receive a bolt that connects the attachment tab to the outer ring.

2. The gas turbine engine of claim 1 , wherein the low pressure turbine comprises a high speed turbine and a counter-rotating low speed turbine.

3. The gas turbine engine of claim 2 , wherein the low speed turbine comprises the rotating drum and the torque frame.

4. The gas turbine engine of claim 1 , wherein the attachment tab extends through an opening in the outer ring that is adjacent a stud that extends radially outward from the outer ring, the stud configured to receive the bolt that connects the attachment tab to the stud.

5. The gas turbine engine of claim 4 , wherein an elongated axis of the bolt extends in a tangential direction with respect to the outer ring.

6. The gas turbine engine of claim 4 , wherein an elongated axis of the bolt extends in an axial direction relative to the outer ring.

7. A gas turbine engine comprising:
a fan located at a forward portion of the gas turbine engine;
a compressor section and a turbine section arranged in serial flow order, the compressor section and the turbine section together defining a core airflow path;
a rotary member rotatable with the fan and with a low pressure turbine of the turbine section;
the low pressure turbine comprising a rotating drum to which a first airfoil structure is connected and extends radially inward toward the rotary member; and
a torque frame that 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 comprising:
an inner disk mounted to the rotary member;
an outer ring formed as a single monolithic piece; and
a second airfoil structure formed separately from the outer ring and connected thereto by a releasable connecting structure configured to extend radially through an outer face of the outer ring, the second airfoil structure extending radially inward from the outer ring toward the inner disk;
wherein the second airfoil structure is part of a structural member that is formed separately from the outer ring and inner disk, the structural member is releasably connected to the outer ring and the inner disk and comprises an outer tip plate that engages the outer ring and an inner tip plate that engages the inner disk;
wherein the outer ring is connected to the outer tip plate by a bolt having an elongated axis that extends radially through the outer ring and into the outer tip plate.

8. A gas turbine engine comprising:
a fan located at a forward portion of the gas turbine engine;
a compressor section and a turbine section arranged in serial flow order, the compressor section and the turbine section together defining a core airflow path;
a rotary member rotatable with the fan and with a low pressure turbine of the turbine section;
the low pressure turbine comprising a rotating drum to which a first airfoil structure is connected and extends radially inward toward the rotary member; and
a torque frame that 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 comprising:
an inner disk mounted to the rotary member;
an outer ring formed as a single monolithic piece; and
a second airfoil structure formed separately from the outer ring and connected thereto by a releasable connecting structure configured to extend radially through an outer face of the outer ring, the second airfoil structure extending radially inward from the outer ring toward the inner disk;
wherein the second airfoil structure is part of a structural member that is formed separately from the outer ring and inner disk, the structural member is releasably connected to the outer ring and the inner disk and comprises an outer tip plate that engages the outer ring and an inner tip plate that engages the inner disk;
wherein a mounting flange extends radially inward from the inner tip plate, the mounting flange of the inner tip plate configured to receive a bolt that connects the mounting flange of the inner disk.

9. The gas turbine engine of claim 8 , wherein the inner disk comprises a corresponding mounting flange configured to receive the bolt that connects the mounting flange of the outer tip plate to the corresponding mounting flange of the inner disk.

10. The gas turbine engine of claim 8 , wherein the bolt comprises an expandable outer peripheral wall.

Assignees

• Gen Electric
• Ge Avio Srl

Inventors

• Alapati Ranganayakulu
• Pankaj Peeyush
• Manepalli Sanjeev Sai Kumar
• Mondal Bhaskar Nanda
• Moniz Thomas
• Emani N V Sai Krishna
• Shah Shishir Paresh
• Soni Anil
• Sharma Praveen
• Antelo Randy T
• D'Ettole Antonio Giuseppe

Classifications

• F02C3/10

  with another turbine driving an output shaft but not driving the compressor · CPC title

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title

• F05D2240/24

  for turbines · CPC title

• F02C3/067 Primary

  having counter-rotating rotors (F02C3/073 takes precedence) · CPC title