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公开(公告)号:US20240253790A1
公开(公告)日:2024-08-01
申请号:US18102510
申请日:2023-01-27
申请人: Rohr, Inc.
IPC分类号: B64D15/00
CPC分类号: B64D15/00 , F02C7/047 , B64D2033/0233 , F05D2300/51 , F05D2300/512
摘要: An air inlet section for an aircraft propulsion system nacelle includes an outer skin, an inner skin, and a lip skin. The lip skin extends between and to an outer end and an inner end. The outer end is disposed at the outer skin. The inner end is disposed at the inner skin. The lip skin forms an exterior lip skin surface extending from the inner end to the outer end. The exterior lip skin surface forms a leading edge of the lip skin. The exterior lip skin surface includes an outer surface portion and an inner surface portion. The outer surface portion extends from the outer end to the inner surface portion. The outer surface portion forms a hydrophobic surface. The inner surface portion extends from the inner end to the outer surface portion. The inner surface portion forms a hydrophilic surface.
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公开(公告)号:US09845728B2
公开(公告)日:2017-12-19
申请号:US14884206
申请日:2015-10-15
申请人: Rohr, Inc.
CPC分类号: F02C7/04 , B23K20/126 , B23K20/129 , B64D33/02 , B64D2033/0206 , B64D2033/0226 , B64D2033/0233 , F01D25/24 , F05D2220/323 , F05D2230/239 , F05D2230/60 , F05D2300/10
摘要: Methods are provided forming a metallic nacelle inlet structure for a turbine engine aircraft propulsion system with an axis. The nacelle inlet structure includes an inlet lip portion and an outer barrel portion. One of the method may include steps of: forming the inlet lip portion; forming the outer barrel portion; arranging the inlet lip portion axially adjacent the outer barrel portion; and friction stir welding the inlet lip portion to the outer barrel portion to provide a circumferentially extending weld joint between the inlet lip portion and the outer barrel portion.
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公开(公告)号:US20170107905A1
公开(公告)日:2017-04-20
申请号:US14884206
申请日:2015-10-15
申请人: Rohr, Inc.
发明人: Keith T. Brown , Vijay V. Pujar , Rusty Hayes , David L. Rose
CPC分类号: F02C7/04 , B23K20/126 , B23K20/129 , B64D33/02 , B64D2033/0206 , B64D2033/0226 , B64D2033/0233 , F01D25/24 , F05D2220/323 , F05D2230/239 , F05D2230/60 , F05D2300/10
摘要: Methods are provided forming a metallic nacelle inlet structure for a turbine engine aircraft propulsion system with an axis. The nacelle inlet structure includes an inlet lip portion and an outer barrel portion. One of the method may include steps of: forming the inlet lip portion; forming the outer barrel portion; arranging the inlet lip portion axially adjacent the outer barrel portion; and friction stir welding the inlet lip portion to the outer barrel portion to provide a circumferentially extending weld joint between the inlet lip portion and the outer barrel portion.
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