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Fan track liner

A fan and track technology, applied in the field of fan track bushings

Active Publication Date: 2020-11-20
ROLLS ROYCE PLC
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] In particular, the containment means may be susceptible to being cut by, rather than crushed by, the metalwork of the fan blade in the event of a fan blade shedding

Method used

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Examples

Experimental program
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Embodiment Construction

[0044] reference figure 1 , The gas turbine engine is generally represented by 10, and has a main axis and a rotation axis 11. The engine 10 includes an axially flowing air inlet 12, a propulsion fan 13, an intermediate pressure compressor 14, a high pressure compressor 15, a combustion device 16, a high pressure turbine 17, an intermediate pressure turbine 18, a low pressure turbine 19 and an exhaust nozzle 20. The nacelle 21 generally surrounds the engine 10 and defines an air inlet 12 and an exhaust nozzle 20.

[0045] The gas turbine engine 10 operates in a conventional manner so that the air entering the air inlet 12 is accelerated by the fan 13 to produce two air streams: the first air stream entering the intermediate pressure compressor 14 and the bypass duct 22 to provide propulsion The second air flow. Before sending the air to the high-pressure compressor 15 for further compression, the intermediate-pressure compressor 14 compresses the air flow directed therein.

[004...

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PUM

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Abstract

There is disclosed a fan track liner assembly (53) for a containment arrangement (50) of a gas turbine engine, the assembly (53) comprising a cellular reactive impact structure (60), wherein cells ofthe reactive impact structure (60) contain a reactive material having shear-thickening or shear-stiffening properties; whereby the reactive impact structure (60) is compliant during assembly to accommodate geometrical non-compliance in the fan track liner assembly.

Description

Technical field [0001] The invention relates to a fan track bushing. Background technique [0002] The known turbofan engine includes a fan facing the upstream end of the engine, the fan including a plurality of blades. Each fan blade is connected to the central fan disc, and in use is driven to rotate by the turbine stage of the corresponding engine. [0003] Generally, such engines include fan blade accommodations arranged circumferentially around the fan. In rare cases, for example, after a foreign object impacts, part or all of the fan blades fall off from the fan tray (fan blade fall-off event), a fan blade accommodation is provided to accommodate the fan blades. [0004] The known containment device includes a housing and a fan track bushing, the fan track bushing comprising a honeycomb material, such as an aluminum honeycomb. During a fan blade shedding event, the fan blade material will hit the honeycomb fan track bushing, and the honeycomb fan track bushing absorbs the en...

Claims

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Application Information

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IPC IPC(8): F01D21/04
CPCF05D2300/43F05D2300/702F05D2300/44F05D2250/183F01D21/045F05D2220/36F05D2230/60F05D2250/11F05D2250/23F05D2250/294F05D2300/501F05D2300/603F05D2300/612F05D2300/6031F05D2300/514F05D2250/283F05D2300/61F05D2300/48Y02T50/60F01D21/04F01D25/005F01D25/285
Inventor 史蒂文·M·霍尔
Owner ROLLS ROYCE PLC
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