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Ice protection system for a multi-segment aircraft component

An aircraft part, anti-icing technology, applied in aircraft parts, ohmic resistance heating parts, heating elements, etc., can solve problems such as damage to the internal engine parts of fans and rotor blades

Active Publication Date: 2014-06-11
THE BF GOODRICH CO +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Additionally, pieces of ice may periodically break off the pod 20 and / or the nose cowl 16 and enter the engine 50, potentially damaging the fan and rotor blades 60 and other internal engine components

Method used

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  • Ice protection system for a multi-segment aircraft component
  • Ice protection system for a multi-segment aircraft component
  • Ice protection system for a multi-segment aircraft component

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0025] Figures 5A-5C One embodiment of an anti-icing heater system according to the present invention is shown, for example, applied to a multi-section pod inlet lip 200 . as in Figure 5A As shown in , the pod inlet lip 200 includes a first inlet lip segment 110 having a first end 222 connected to a second end of the second inlet lip segment 112 along a joint 211 . End 226. The joint 211 can include a narrow gap 220 between the segment ends 222 , 226 . The first inlet lip segment 110 can include a first embedded heating element 223 adjacent the first end 222 and the second inlet lip segment 112 can include a second embedded heating element adjacent the second end 226. Element 227. as in Figure 5A As shown in , the joined inlet lip segments 110 , 112 can form a substantially continuous outer surface in the region immediately adjacent the joint 211 and the gap 220 . Figure 5B with 5C Details of one embodiment of joint 211 are shown.

[0026] as in Figure 5B with 5...

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PUM

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Abstract

An aircraft component is disclosed which comprises a first segment (110) comprising a first exterior surface, a first end (222), and a first electric heater element (223) having a first edge proximate to the first end; a second segment (112) comprising a second exterior surface, a second end (226), and a second electric heater element (227) having a second edge proximate to the second end (226), wherein the second end is joined (211) to the first end such that the first external surface and the second external surface combine to form at least a portion of a substantially continuous leading edge surface; a first bus bar (230) connected to the first edge of the first heater element; and a second bus bar (230) connected to the second edge of the second heater element; wherein the first and second bus bars are disposed between the first end and the second end when the first end is joined to the second end.

Description

technical field [0001] The present invention relates generally to anti-icing systems for aircraft, and more particularly to anti-icing systems for selectively heating leading edge surfaces of aircraft components, including portions of leading edge surfaces proximate structural joints of said aircraft components. icing system. Background technique [0002] The leading edges of aircraft engine nacelles and other aircraft components are prone to icing. FIG. 1 shows a schematic diagram of a typical high speed jet engine assembly 10 . Air enters through the inlet section 14 between a fan blade spinner 16 and an annular casing 18 , which constitutes the forwardmost part of the nacelle 20 and includes a nacelle inlet lip 21 . Hot, high pressure propellant gas passes through compressor section 17 and an exhaust assembly (not shown) at the rear of the nacelle. Bulkhead 28 and annular shell 18 define an annular space and a D-channel 30 . A bulkhead 28 separates the D-channel 30 fr...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64D15/12B64D33/02F02C7/047F02C7/045H05B3/28B64D15/14
CPCB64D33/02B64D2033/0233B64D2033/0206F02C7/045Y02T50/672B64D15/12F02C7/047H05B3/06F05D2250/132Y10T29/49826Y02T50/60
Inventor 约瑟夫·C·泽卡加尔德米尔·C·伯图拉布赖恩·B·伯克特克劳德·M·赫伯特迈克尔·J·莱兰蒂莫西·R·奥尔森詹姆斯·M·罗曼
Owner THE BF GOODRICH CO