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Windage shield

a windage shield and shield technology, applied in the field of windage shields, can solve the problems of reducing engine efficiency and harmful out-of-balance vibration effects, and achieve the effect of less balancing weigh

Inactive Publication Date: 2020-05-28
ROLLS ROYCE PLC
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

The patent text suggests placing weights on the fan disc where it is attached to the engine's windage shield. This may help to keep the fan disc balanced while it is running.

Problems solved by technology

This sets up a recirculation which can reduce engine efficiency.
Harmful out-of-balance vibrational effects can be caused by an uneven distribution of mass about an axis of rotation of the fan disc (i.e. an imbalanced fan).

Method used

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Examples

Experimental program
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Embodiment Construction

[0062]FIG. 1 illustrates a gas turbine engine 10 having a principal rotational axis 9. The engine 10 comprises an air intake 12 and a propulsive fan 23 that generates two airflows: a core airflow A and a bypass airflow B. The gas turbine engine 10 comprises a core 11 that receives the core airflow A. The engine core 11 comprises, in axial flow series, a low pressure compressor 14, a high-pressure compressor 15, combustion equipment 16, a high-pressure turbine 17, a low pressure turbine 19 and a core exhaust nozzle 20. A nacelle 21 surrounds the gas turbine engine 10 and defines a bypass duct 22 and a bypass exhaust nozzle 18. The bypass airflow B flows through the bypass duct 22. The fan 23 is attached to and driven by the low pressure turbine 19 via a shaft 26 and an epicyclic gearbox 30.

[0063]In use, the core airflow A is accelerated and compressed by the low pressure compressor 14 and directed into the high pressure compressor 15 where further compression takes place. The compres...

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PUM

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Abstract

A fan rotor module for a gas turbine engine, the fan rotor module comprising a drive arm, a fan disc and a windage shield attached at one or more points to a rear portion of the fan disc, wherein the fan rotor module comprises at least one balancing weight disposed at one or more of the points where the windage shield is attached to the rear portion of the fan disc.

Description

CROSS-REFERENCE TO RELATED APPLICATIONS[0001]This specification is based upon and claims the benefit of priority from United Kingdom patent application number GB 1819251.8 filed on Nov. 27, 2018, the entire contents of which are incorporated herein by reference.BACKGROUNDField of the Disclosure[0002]The present disclosure relates to a windage shield for mounting on a rotor disc of a fan of a gas turbine engine, a fan of a gas turbine engine and a gas turbine engine.Description of the Related Art[0003]Gas turbine engines include a fan at the front of the engine. The fan comprises a plurality of radially extending blades mounted on a rotor disc which rotates about an axis. The fan is used as a first compression stage for air passed to a combustor, and to direct air passing through a by-pass to provide thrust. Further compression stages for the air provided to the combustor may also use rotating compressors, having a plurality of blades extending from a hub.[0004]Rotation of a fan caus...

Claims

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Application Information

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Patent Type & Authority Applications(United States)
IPC IPC(8): F01D25/24F01D11/00
CPCF05D2220/323F02K3/06F01D5/066F05D2260/31F05D2230/60F01D11/001F01D25/243F02C7/04F05D2240/20F05D2260/97F05D2220/36F02C7/28F01D5/027F04D29/321F04D29/662Y02T50/60
Inventor BREEN, CLIVE
Owner ROLLS ROYCE PLC