Wing leading edge architecture suitable for laminar flow

US9896190B1 · kind B1 · utility

Assignee

• The Boeing Company · US

Inventors

• Stephen R. Amorosi · Seattle, US
• Gregory M. Santini · Bothell, US
• Matthew L. Anderson · Salem, US
• Steve C. Hinrichs · Cypress, US
• Walter J. Jarecki · Chino Hills, US
• Nicholas I. Bennett · Seattle, US
• Quang Minh Pham · Palmdale, US
• Paul H. Lai · Arcadia, US
• Gregory E. Rupert · Rossmoor, US
• Carl F. Osaki · Long Beach, US

Key dates

• Filing date: May 7, 2014
• Grant date: Feb 20, 2018
• Expiry date: Jul 31, 2036

Classification

• Technology area (CPC Y): Emerging Cross-Sectional Technologies
• CPC primary: Y02T50/30
• WIPO field: Transport
• WIPO sector: Mechanical engineering

Abstract

A wing leading edge architecture designed to enable laminar flow on passenger jets or other aircraft. The embodiments disclosed herein comprise a metallic fixed leading edge skin panel that is bonded to internal support structure without fasteners except for limited fastening along side edge portions adjacent to side edge portions of adjacent leading edge skin panels and along an aft edge portion overlapping a wing skin. In addition, the embodiments disclosed herein integrate a low-drag bleed-air anti-icing (i.e., vent) system and a Krueger flap assembly (e.g., a two-position, high-height, variable-camber Krueger flap assembly).