Turbofan case and method of making

Inactive Publication Date: 2007-10-18
PRATT & WHITNEY CANADA CORP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

[0016] In accordance with a further aspect of the present invention, there is provided a casing for an aircraft turbofan bypass engine, the casing comprising a case adapted to encircle the engine and having a plurality of engine mounts thereon adapted to mount the engine to an aircraft; a plurality of struts extending between an engine structure and the case, the struts defining a primary load path from the engine structure to the case for transfer

Problems solved by technology

Simply scaling down larger conventional turbofan engines, however, presents difficulties due mainly to the disproportionate scaling of certain factors, such as strength-to-weight and tolerances.
These asymmetric loads result in bending moments and shears which must be

Method used

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  • Turbofan case and method of making
  • Turbofan case and method of making
  • Turbofan case and method of making

Examples

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Embodiment Construction

[0033] Referring to the drawings, beginning with FIG. 3, an exemplary turbofan gas turbine engine 10 according to the present invention includes in serial flow communication about a longitudinal central axis 12, a fan assembly 13 having a plurality of circumferentially spaced fan blades 14, a compressor section 16 having a plurality of circumferentially spaced low pressure compressor (LPC) blades 50 and high pressure compressor (HPC) blades 51, a diffuser 18, a combustor 20, a high pressure turbine (HPT) 22, and a low pressure turbine (LPT) 24. LPT 24 is connected to the fan assembly 13 by a first or low pressure (LP) shaft 26, and HPT 22 is connected to compressor assembly 16 by a second or high pressure (HP) shaft 28. Fuel injecting means 30 are provided for injecting fuel into the combustor 20

[0034] A generally tubular casing assembly 32 having a envelops the engine 10 and thereby defines a main flow path 36 through the core of engine 10, extending from an inlet 34 to an exhaust ...

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Abstract

A casing for a gas turbine includes a construction providing improved structural efficiency. Improved load paths and means for transmitting loads in the engine case are disclosed.

Description

CROSS-REFERENCE [0001] This application is a division of pending application Ser. No. 10 / 883,987, filed Jul. 6, 2004 which is a continuation in part of application Ser. No. 10 / 628,556, filed Jul. 29, 2003FIELD OF THE INVENTION [0002] This invention relates to gas turbine engines, and more particularly to a case for a turbofan engine. BACKGROUND OF THE INVENTION [0003] The general aviation market has recently been introduced to the “very small” turbofan engine (i.e. 2000 pounds thrust and less). Simply scaling down larger conventional turbofan engines, however, presents difficulties due mainly to the disproportionate scaling of certain factors, such as strength-to-weight and tolerances. [0004] The engine case, such as that depicted in FIGS. 1 and 2, is subjected to asymmetric loading relative to the engine mounts, caused by loads exerted through the bearings, such as engine thrust, foreign object impacts and blade-off events, and caused by inertia loads caused by the engine weight wh...

Claims

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Application Information

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IPC IPC(8): B64D27/00F01D5/22F01D25/24F02K3/06
CPCF01D25/162F01D25/24F02C7/20F05D2230/60F05D2240/122F05D2240/304Y02T50/671F02K3/06
InventorELEFTHERIOU, ANDREASLOBO, KEVIN WALTERWEINBERG, MAURICELIU, QUANTAI
OwnerPRATT & WHITNEY CANADA CORP