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Gas turbine engine blade containment using wire wrapping

Inactive Publication Date: 2009-04-30
PRATT & WHITNEY CANADA CORP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

[0005]In another aspect, the present invention provides a gas turbine engine which comprises at least a compressor assembly, a gas generation assembly, a turbine assembly and a fan assembly, the fan assembly including a fan rotor having a plurality of radially extending blades, and a casing defining an annular wall immediately surrounding the blades with a clearance therebetween, the annular wall including a means for reinforcing fan blade containment of the fan assembly, said mea

Problems solved by technology

However, these conventional blade containment techniques involve either configurations with a significant weight penalty or polymer-bonded fiber web layers which disadvantageously absorb moisture and thus degrade severely under stress and which must also be protected from abrasion or cutting during handling.

Method used

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  • Gas turbine engine blade containment using wire wrapping
  • Gas turbine engine blade containment using wire wrapping
  • Gas turbine engine blade containment using wire wrapping

Examples

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Embodiment Construction

[0012]FIG. 1 illustrates an exemplary turbofan gas turbine engine 10 which includes an outer casing 28, a core casing 30, a low pressure spool assembly seen generally at 12 which includes a fan assembly 14 and a low pressure turbine assembly 18 and a high pressure spool assembly seen generally at 20 which includes a high pressure compressor assembly 22 and a high pressure turbine assembly 24. The core casing 30 surrounds the low and high pressure spool assemblies 12 and 20 in order to define a main fluid path (not indicated) therethrough, which includes a combustor 26 to form a gas generation assembly (not indicated).

[0013]Referring to FIGS. 1-3, the fan assembly 14 includes a fan rotor 32 which may be cylindrical or truncated conical and is mounted to a shaft 34 of the low pressure spool assembly 12. A plurality of fan blades 36 are mounted to the fan rotor 32 and extend radially outwardly therefrom. A fan casing 38 is provided to define an annular wall 40 radially spaced apart fro...

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PUM

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Abstract

A blade containment of a gas turbine engine comprises a casing defining an annular wall radially spaced from and immediately surrounding a plurality of blades radially extending from a rotor, and at least one layer of metal wires wrapped around and directly attached to the annular wall.

Description

TECHNICAL FIELD[0001]The invention relates generally to gas turbine engines and, more particularly, to an improved blade containment assembly for use in gas turbine engines.BACKGROUND OF THE ART[0002]Turbofan gas turbine engines for powering aircraft conventionally comprise a core engine which drives a fan. The fan includes a plurality of fan blades radially extending from a fan rotor and surrounded by a generally cylindrical or truncated conical fan casing. The fan casing functions not only as an outer boundary of an annular passage for directing air flow to pass through and be driven by the fan blades, but also as a containment to prevent any broken-off fan fragments from breaking through the engine casing when a failure of the fan blades occurs in order to avoid serious consequences to the aircraft itself. Fan blade containment has been conventionally accomplished using many different techniques such as thick walled aluminium casings, thick walled steel casings, or thinner walled...

Claims

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Application Information

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IPC IPC(8): F01B25/16
CPCY02T50/671F01D21/045Y02T50/60
Inventor KOSTKA, RICHARD A.URAC, TIBOR
Owner PRATT & WHITNEY CANADA CORP