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
CN104246147AActive Publication Date: 2014-12-24EATON INTELLIGENT POWER LTD
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
EATON INTELLIGENT POWER LTD
Publication Date
2014-12-24

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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.
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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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