Aircraft engine fuel pump bearing flow and associated system and method

An aero-engine and engine technology, which is applied in the direction of engine lubrication, turbine/propulsion fuel delivery system, charging system, etc., and can solve problems such as pressure increase

Active Publication Date: 2014-12-24
EATON INTELLIGENT POWER LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

For example, when the engine accelerates, the pressure builds up and is limited by the action of the pressure relief valve which is set low based on the low pressure bearing supply

Method used

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  • Aircraft engine fuel pump bearing flow and associated system and method
  • Aircraft engine fuel pump bearing flow and associated system and method
  • Aircraft engine fuel pump bearing flow and associated system and method

Examples

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Embodiment Construction

[0027] figure 1 A typical pump that provides a constant supply of bearing lubrication flow to the radial bearings of a pump, such as a high pressure stage pump. More particularly, system 100 includes a first or booster stage pump 110, shown schematically as a centrifugal pump. Fluid enters at 112 to booster stage pump 110 , which is rotated by drive shaft 114 . The output 116 from the boost stage pump 110 is provided to a second or high pressure stage pump 120 downstream of the boost stage. High pressure pump 120 is also driven by shaft 114 . Reference signal 122 is also provided from outlet 116 of booster stage pump 110 to pressure relief valve 130 . Pressure relief valve 130 is biased toward the closed position by means of a biasing member, such as spring 132 . Pressure relief valve 130 receives flow from high pressure pump 120 and if the pressure of the output flow from the high pressure pump provides a force that exceeds the combined signal 122 from booster stage pump ...

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PUM

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Abstract

An assembly or system is provided for selectively regulating journal bearing lubrication between at least first and second levels in an aircraft engine. A high pressure pump includes movable portions at least in part supported by a journal bearing. A selector valve is configured to selectively supply lubrication flow to the journal bearing. In addition, a relief valve is configured to receive a signal from the selector valve defining a pressure level at which the relief valve should relieve pressure.

Description

technical field [0001] The present invention relates to fuel pumps, and to fuel pumps for use in aircraft engines. More particularly, the present invention relates to a system and method for providing adequate and reliable fluid flow to radial bearings (journal bearings) of a fuel pump during different operating modes. Background technique [0002] Aeroengine fuel pumps are often sized during engine start conditions, ie, when the windmill is refiring. Using this parameter for design purposes results in an unnecessarily oversized fuel pump under other conditions. By shutting off radial bearing lubrication flow, more flow can be delivered at the outlet of the pump. However, the radial bearing lubrication flow must be turned on again under high speed / high pressure conditions. There is (thus) a need for a reliable assembly and method of closing and opening this (lubrication) flow. [0003] Furthermore, it is desirable to avoid running the pump at higher speed / higher pressure...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D25/20
CPCF02C7/06F02C7/232Y02T50/60Y10T137/85954
Inventor M·A·克莱蒙茨
Owner EATON INTELLIGENT POWER LTD
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