公开(公告)号：US20200023988A1

公开(公告)日：2020-01-23

申请号：US16042024

申请日：2018-07-23

Applicant: Bell Helicopter Textron Inc.

Inventor： Thomas Dewey Parsons ,  Angel David Rosado ,  Robert Paul Reynolds ,  David Frank Haynes ,  William Mathisen Gons

IPC: B64D33/08 ,  B64D33/02 ,  F15D1/00

Abstract: A boundary layer utilization apparatus for intake of air to a high speed aircraft, comprises a first air inlet adjacent an exterior surface of a fuselage of the aircraft and offset from the fuselage enough to integrate a second air inlet in the offset space to ingest and divert the boundary layer air flowing next to the fuselage into the aircraft for a useful purpose such as cooling the engine compartment. The second air inlet is disposed aft of the first air inlet to minimize hot gas re-ingestion.

公开(公告)号：US20190241251A1

公开(公告)日：2019-08-08

申请号：US15887664

申请日：2018-02-02

Applicant: Bell Helicopter Textron Inc.

Inventor： Brady Garrett Atkins ,  Robert Paul Reynolds ,  Carlos Alexander Fenny ,  Charles Eric Covington

IPC: B64C11/38 ,  F01B25/10 ,  F01B9/00

CPC classification number: F16K31/047 ,  F16K11/20

Abstract: Systems and methods include providing an aircraft with a direct drive dual-concentric valve (D3V) having a body, an outer secondary spool coaxially located within a bore of the body and linearly displaceable relative to the body, an inner primary spool coaxially located within a bore of the secondary spool and linearly displaceable relative to the secondary spool and the body, and multiple motor assemblies coupled to the primary spool that provide selective displacement of the primary spool or the secondary spool. Each motor assembly includes a clutching mechanism that selectively couples a motor of the motor assembly to and from the primary spool.

公开(公告)号：US20180274563A1

公开(公告)日：2018-09-27

申请号：US15466655

申请日：2017-03-22

Applicant: Bell Helicopter Textron Inc.

Inventor： Carl Theodore Elving ,  Robert Paul Reynolds ,  David Alan Hawthorne ,  Carlos Alexander Fenny

IPC: F15B11/17 ,  F15B1/26 ,  B64D29/02 ,  B64C29/00 ,  B64C13/36

CPC classification number: F15B11/17 ,  B64C13/36 ,  B64C13/40 ,  B64C13/42 ,  B64C27/28 ,  B64C29/0033 ,  B64D29/02 ,  B64D41/00 ,  F15B1/26 ,  F15B18/00 ,  F15B2211/20507 ,  F15B2211/20523 ,  F15B2211/20576 ,  F15B2211/7142 ,  Y02T50/44

Abstract: A hydraulic system for an aircraft having an engine and an auxiliary power unit includes a first hydraulic subsystem including a first hydraulic pump and a first set of hydraulic-powered components in fluid communication with the first hydraulic pump. The first hydraulic pump is powered by the engine to pump shared hydraulic fluid to the first set of hydraulic-powered components. The hydraulic system includes a second hydraulic subsystem including a second hydraulic pump and a second set of hydraulic-powered components in fluid communication with the second hydraulic pump. The second hydraulic pump is powered by the auxiliary power unit to pump the shared hydraulic fluid to the second set of hydraulic-powered components. A shared return line subsystem and reservoir is in fluid communication with the first and second hydraulic subsystems to return the shared hydraulic fluid to the first and second hydraulic pumps.