Air divider ring structure for jet engine inlet air duct

Claim 2

An inlet air divider ring for a jet engine comprising: a plurality of longerons mounted within the inlet duct of a jet engine at selected, equal, radial disTances from the longitudinal axis of the intake duct, said longerons comprising segments of a streamlined air divider ring disposed coaxially of the inlet duct; a panel-mounting half element having a plurality of perforated, aligned, spaced-apart abutments thereon mounted along each lateral edge of each longeron; a curved panel of sound absorptive material comprising a complementary segment of such streamlined air divider ring fitted between each two adjacent longerons; a panel-mounting other half element having a plurality of perforated, spaced-apart abutments thereon mounted along each lateral edge of each panel with the abutments thereof fitted in interdigitated relation between the abutments on the panel mounting half element on the longeron laterally adjacent thereto, the perforations in both pluralities of interdigitated abutments being aligned; and a fastening pin inserted through the aligned perforations in the abutments of each longeron-mounted half element and the interdigitated abutments of its associated other half element to attach the panels in complementary relation to the longerons.

Claim 3

An inlet air divider ring as claimed in claim 1 wherein an equal plurality of said longerons are mounted at symmetrically radially spaced intervals within said inlet duct with each plurality of corresponding longerons comprising a set of longerons, the longerons of each set being spaced equally from the air inlet duct axis and comprising segments of a streamlined air divider ring, and a said panel comprising a supplemental segment of each such divider ring is fitted between each two adjacent longerons of each set of longerons to form a plurality of coaxial, streamlined air divider rings mounted coaxially within the air inlet duct.

Claim 4

An inlet air divider ring for a jet engine comprising: a plurality of generally radially extending struts mounted within the air inlet duct of a jet engine nacelle; a longeron mounted on each strut at a common radial distance from the longitudinal axis of the intake duct, said longerons comprising segments of a streamlined air divider ring disposed coaxially within the inlet duct; a plurality of perforated panel mounting abutments secured in spaced-apart, aligned relation along each lateral edge of each longeron; a curved honeycomb panel comprising a complementary segment of such streamlined air divider ring fitted between each two adjacent longerons, each panel comprising a layer of honeycomb core material, a backing layer of sheet material of substantial structural strength on one end of said core material, and a sound pervious facing on the other end of said core material; another plurality of perforated abutments secured in aligned relation along each lateral edge of each said backing sheet, each plurality of said other abutments being spaced-apart and fitted in interdigitated relation between the abutments of a longeron laterally adjacent thereto with the perforations in both pluralities of interdigitated abutments aligned; and a fastening pin inserted through the aligned perforations of each such two pluralities of interdigitated abutments.

Claim 5

An inlet air divider ring for a jet engine comprising: a plurality of generally radially extending struts mounted within the air inlet duct of a jet engine nacelle; a longeron mounted on each strut at a common radial distance from the longitudinal axis of the intake duct, said longerons comprising segments of a streamlined air divider ring disposed coaxially within the inlet duct; a plurality of perforated panel mounting abutments secured in spaced-apart, aligned relation along each lateral edge of each longeron; a curved honeycomb panel comprising a complementary segment of such streamlined air divider ring fitted between each two adjacent longerons, each panel comprising a layer of honeycomb core material, a backing layer of sheet material of substantial structural strength on one end of said core material, and a sound pervious facing on the other end of said core material; another plurality of perforated abutments secured in aligned relation along each lateral edge of each said backing sheet, each plurality of said other abutments being spaced-apart and fitted in interdigitated relation between the abutments of a longeron laterally adjacent thereto with the perforations in both pluralities of interdigitated abutments aligned; and a fastening pin inserted through the aligned perforations of each such two pluralities of interdigitated abutments.

Claim 6

An inlet air divider ring as claimed in claim 3 wherein each honeycomb panel comprises a central layer of relatively heavy sheet material of substantial structural strength and stiffness, a layer of honeycomb core material is applied to each side of said central layer, a sound pervious facing is provided on the outer end of each layer of core material, and said latter abutments are secured in aligned relation along each lateral edge of the central layer of each panel.

Claim 7

An inlet air divider ring as claimed in claim 3 wherein an annular nose fairing is fitted in conforming relation into the upstream ends of said longerons and said panels in position to cover the upstream ends of said pins and restrain them from forward displacement.

Claim 8

An inlet air divider as claimed in claim 5 wherein the nose fairing ring is assembled from a plurality of Supplemental segments, one segment being mounted on the upstream end of each longeron, and one segment being mounted on the upstream end of each panel, selected ones of said segments being removable.

Claim 9

An inlet air divider ring as claimed in claim 3 wherein a tail fairing is fitted in conforming relation onto the downstream ends of said longerons and said panels.

Claim 10

An inlet air divider ring as claimed in claim 7 wherein the tail fairing is assembled from a plurality of supplemental segments, one segment being mounted on the downstream end of each longeron and one segment being mounted on the downstream end of each panel, selected ones of said segments being removable.