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Rotor thrust balancing apparatus and method

a technology of thrust bearing and rotor, which is applied in the direction of mechanical equipment, machines/engines, etc., can solve the problems of premature failure of thrust bearings, deterioration of engine operating characteristics, and affecting the operation of the engin

Inactive Publication Date: 2007-05-31
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

"The patent describes an apparatus and method for balancing thrust bearing load on a rotor thrust bearing. It uses two balance piston cavities to exert thrust balancing forces in opposite directions. By controlling air pressure in each cavity, the apparatus can independently control the balancing force in each direction, resulting in improved performance and efficiency of the engine."

Problems solved by technology

If net axial thrust is excessive, considerable wear and premature failure of the thrust bearing may occur.
If cross-over occurs, unloaded ball bearings may allow radial movement of the rotor which may adversely affect seal clearances resulting in deterioration of engine operating characteristics.

Method used

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  • Rotor thrust balancing apparatus and method
  • Rotor thrust balancing apparatus and method
  • Rotor thrust balancing apparatus and method

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Embodiment Construction

[0012] Referring now to the drawings in detail, wherein identical numerals indicate the same elements throughout the figures, and in which “upstream” indicates a direction toward the engine air intake, and “downstream” indicates a direction toward the engine exhaust, FIG. 1 schematically depicts an aeroderivative gas turbine engine 10. Engine 10 comprises in axial alignment in serial flow sequence a low pressure compressor 12, a high pressure compressor 14, a combustor 16, a high pressure turbine 18, and a low pressure turbine 20, disposed concentrically about longitudinal axis 22. The standard configuration for engines of this type is a dual concentric shaft arrangement, in which low pressure turbine 20 is drivingly connected to low pressure compressor 12 by low pressure drive shaft 24 and is typically connected to a load (not shown) at its downstream end 29. High pressure turbine 18 is similarly drivingly connected to high pressure compressor 14 by high pressure drive shaft 26 dis...

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Abstract

Apparatus and method of balancing thrust bearing load on a rotor thrust bearing employ a first thrust balance piston cavity for exerting an aft directed thrust balancing force and a second balance piston cavity for exerting an independently controlled forward directed thrust balancing force to allow flexible and wide range balancing of thrust load on the rotor thrust bearing.

Description

BACKGROUND OF THE INVENTION [0001] This invention relates generally to a system for balancing loads on a thrust bearing of a gas turbine engine, and more particularly, to a system for increasing the range of control for rotor thrust balancing. [0002] Gas turbine engines include a rotor assembly which is rotatable relative to stationary engine structures, including rotor mounting structure The rotor assembly includes a number of rotatable components, such as a central shaft, shaft cones, compressor blades and disks, turbine buckets and wheels, and dynamic air seals. Each component is reacted upon by static and / or dynamic axial pressure forces. The vector sum of these forces is a net axial force or thrust in either the forward or aft direction. This net thrust places axial loads on the stationary mounting structure, and a thrust bearing is employed in order to absorb this load without interfering with the free rotation of the rotor assembly. Typically, a rotor thrust bearing is a ball...

Claims

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Application Information

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Patent Type & Authority Applications(United States)
IPC IPC(8): F01D3/04
CPCF01D3/04F05D2240/52
Inventor ANSARI, AMIDCHOUINARD, EMIL NELSONSTIFTAR, EDWARD JOSEPH
Owner GENERAL ELECTRIC CO