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Rotor assembly for gas turbines

A technology for gas turbines and turbine rotors, which can be used in engine components, blade support components, mechanical equipment, etc., and can solve problems such as limited torque.

Inactive Publication Date: 2013-01-16
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, due to this radial pin configuration, the torque that can be transmitted through the pin is very limited

Method used

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  • Rotor assembly for gas turbines
  • Rotor assembly for gas turbines
  • Rotor assembly for gas turbines

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Embodiment Construction

[0056] Reference will now be made in detail to embodiments of the invention, one or more examples of which are illustrated in the accompanying drawings. Each example is given by way of explanation of the invention, not limitation of the invention. In fact, it will be apparent to those skilled in the art that various modifications and variations can be made in the present invention without departing from the scope or spirit of the invention. For example, features illustrated or described as part of one embodiment can be used with another embodiment to yield a still further embodiment. Thus, it is intended that the present invention covers such modifications and variations as come within the scope of the appended claims and their equivalents.

[0057] Generally, the present invention relates to a rotor assembly including one or more axial torque pins extending between adjacent rotor disks of the rotor assembly. Torque pins may generally be configured to transmit torque between...

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Abstract

A rotor assembly (100) is disclosed. The rotor assembly (100) may include a first rotor disk (102) defining a first axially extending slot (114) and a second rotor disk (104) defining a second axially extending slot (116). Additionally, the rotor assembly (100) may include a pin (108) extending lengthwise between the first and second rotor disks (102, 104). The pin (108) may include a first end (110) terminating within the first axially extending slot (114) and a second end (112) terminating within the second axially extending slot (116). A corresponding gas turbine engine (10) is also disclosed.

Description

technical field [0001] The present invention relates generally to rotor assemblies for gas turbines, and more particularly to one or more axial torque pins extending between adjacent rotor disks of a rotor assembly for transferring torque between the rotor disks . Background technique [0002] A gas turbine typically includes a compressor section, a combustion section, and a turbine section. The compressor stages pressurize the air flowing into the turbine. Pressurized air discharged from the compressor section flows into the combustion section, which may be characterized by a plurality of combustors arranged in an annular array about the axis of the engine. The pressurized air entering each combustor is mixed with fuel and combusted. Hot combustion gases flow through the transition piece from the combustion section to the turbine section of the gas turbine to drive the turbine and generate electricity. [0003] The rotating structure of a gas turbine is generally referr...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D5/06
CPCF01D5/066F05D2250/13
Inventor C.E.米勒
Owner GENERAL ELECTRIC CO
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